xflr5 v6.59 points1.0000000 0.0000000 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -42.000 0.376 -0.578 0.098 1.000 0.147 0.0000 -0.6361 Cpi Cpv ----------------- -0.1312 -0.2727 -0.0263 -0.2727 0.6369 -0.2720 0.6242 -0.2707 0.6105 -0.2687 0.6008 -0.2657 0.5928 -0.2613 0.5866 -0.2550 0.5824 -0.2465 0.5796 -0.2356 0.5785 -0.2223 0.5787 -0.2067 0.5802 -0.1890 0.5831 -0.1697 0.5873 -0.1490 0.5928 -0.1272 0.5995 -0.1046 0.6076 -0.0814 0.6171 -0.0575 0.6281 -0.0331 0.6407 -0.0081 0.6549 0.0177 0.6708 0.0445 0.6887 0.0725 0.7084 0.1019 0.7302 0.1330 0.7539 0.1662 0.7795 0.2016 0.8068 0.2396 0.8356 0.2803 0.8654 0.3240 0.8955 0.3707 0.9249 0.4205 0.9522 0.4733 0.9757 0.5288 0.9928 0.5868 1.0000 0.6466 0.9925 0.7075 0.9638 0.7682 0.9045 0.8276 0.8010 0.8830 0.6333 0.9327 0.3706 0.9718 -0.0363 0.9961 -0.6692 0.9967 -1.6719 0.9622 -3.3135 0.8714 -6.1349 0.6939 -11.3274 0.3761 -21.7226 -0.1319 -44.5545 -0.6361 -87.9516 -0.5056 -92.7007 -0.4701 -55.1635 -0.4711 -32.7201 -0.4730 -21.1133 -0.4719 -14.6049 -0.4688 -10.6408 -0.4650 -8.0495 -0.4616 -6.2577 -0.4585 -4.9624 -0.4354 -3.9923 -0.4055 -3.2446 -0.3873 -2.6548 -0.3733 -2.1807 -0.3617 -1.7935 -0.3518 -1.4732 -0.3431 -1.2053 -0.3353 -0.9792 -0.3283 -0.7868 -0.3220 -0.6220 -0.3163 -0.4800 -0.3111 -0.3569 -0.3064 -0.2498 -0.3021 -0.1561 -0.2983 -0.0738 -0.2948 -0.0013 -0.2917 0.0629 -0.2889 0.1200 -0.2864 0.1709 -0.2842 0.2165 -0.2823 0.2575 -0.2806 0.2945 -0.2791 0.3281 -0.2778 0.3587 -0.2768 0.3867 -0.2759 0.4126 -0.2751 0.4365 -0.2745 0.4588 -0.2741 0.4798 -0.2737 0.4998 -0.2734 0.5190 -0.2731 0.5378 -0.2730 0.5566 -0.2729 0.5756 -0.2728 0.5964 -0.2727 0.6199 -0.2727 0.6450 -0.2727 0.7301 -0.2727 -0.1312 -0.2727 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -41.500 0.375 -0.578 0.096 1.000 0.151 0.0000 -0.6350 Cpi Cpv ----------------- -0.1467 -0.2740 -0.0404 -0.2739 0.6318 -0.2733 0.6190 -0.2721 0.6050 -0.2701 0.5951 -0.2672 0.5869 -0.2629 0.5805 -0.2568 0.5760 -0.2485 0.5731 -0.2379 0.5717 -0.2250 0.5717 -0.2097 0.5730 -0.1925 0.5757 -0.1737 0.5796 -0.1534 0.5848 -0.1322 0.5914 -0.1101 0.5992 -0.0873 0.6085 -0.0640 0.6192 -0.0401 0.6315 -0.0156 0.6455 0.0097 0.6613 0.0360 0.6789 0.0634 0.6986 0.0923 0.7202 0.1229 0.7439 0.1556 0.7695 0.1905 0.7970 0.2280 0.8261 0.2683 0.8563 0.3116 0.8870 0.3580 0.9173 0.4076 0.9458 0.4603 0.9708 0.5159 0.9898 0.5740 0.9995 0.6341 0.9953 0.6955 0.9706 0.7570 0.9164 0.8174 0.8196 0.8741 0.6604 0.9257 0.4089 0.9670 0.0171 0.9941 -0.5951 0.9982 -1.5682 0.9680 -3.1655 0.8826 -5.9168 0.7114 -10.9896 0.4002 -21.1617 -0.1060 -43.5388 -0.6350 -86.1655 -0.5134 -91.0059 -0.4749 -54.2462 -0.4751 -32.2203 -0.4767 -20.8161 -0.4755 -14.4152 -0.4723 -10.5132 -0.4685 -7.9604 -0.4649 -6.1939 -0.4619 -4.9159 -0.4433 -3.9582 -0.4100 -3.2194 -0.3910 -2.6363 -0.3765 -2.1672 -0.3646 -1.7840 -0.3544 -1.4667 -0.3454 -1.2012 -0.3375 -0.9769 -0.3304 -0.7860 -0.3239 -0.6224 -0.3181 -0.4814 -0.3129 -0.3591 -0.3081 -0.2526 -0.3038 -0.1595 -0.2999 -0.0777 -0.2964 -0.0055 -0.2932 0.0584 -0.2904 0.1152 -0.2878 0.1659 -0.2856 0.2113 -0.2836 0.2521 -0.2819 0.2890 -0.2804 0.3225 -0.2792 0.3530 -0.2781 0.3810 -0.2772 0.4068 -0.2765 0.4306 -0.2758 0.4530 -0.2753 0.4740 -0.2750 0.4939 -0.2747 0.5132 -0.2744 0.5321 -0.2743 0.5509 -0.2741 0.5702 -0.2741 0.5911 -0.2740 0.6149 -0.2740 0.6402 -0.2740 0.7264 -0.2740 -0.1467 -0.2740 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -41.000 0.374 -0.578 0.093 1.000 0.154 0.0000 -0.6336 Cpi Cpv ----------------- -0.1621 -0.2753 -0.0544 -0.2753 0.6269 -0.2747 0.6137 -0.2735 0.5996 -0.2716 0.5894 -0.2687 0.5810 -0.2646 0.5744 -0.2586 0.5697 -0.2506 0.5665 -0.2403 0.5649 -0.2277 0.5647 -0.2129 0.5658 -0.1961 0.5683 -0.1776 0.5720 -0.1579 0.5769 -0.1371 0.5832 -0.1155 0.5908 -0.0933 0.5998 -0.0705 0.6103 -0.0471 0.6223 -0.0231 0.6361 0.0017 0.6517 0.0275 0.6691 0.0544 0.6886 0.0828 0.7101 0.1129 0.7337 0.1450 0.7594 0.1794 0.7870 0.2165 0.8163 0.2564 0.8469 0.2993 0.8782 0.3454 0.9093 0.3947 0.9390 0.4473 0.9655 0.5028 0.9864 0.5611 0.9985 0.6215 0.9974 0.6834 0.9767 0.7456 0.9276 0.8070 0.8373 0.8651 0.6866 0.9184 0.4462 0.9618 0.0693 0.9917 -0.5224 0.9993 -1.4661 0.9732 -3.0194 0.8931 -5.7011 0.7282 -10.6548 0.4236 -20.6046 -0.0806 -42.5278 -0.6336 -84.3843 -0.5237 -89.3126 -0.4820 -53.3281 -0.4813 -31.7192 -0.4826 -20.5177 -0.4812 -14.2243 -0.4779 -10.3845 -0.4741 -7.8704 -0.4705 -6.1293 -0.4673 -4.8688 -0.4529 -3.9234 -0.4152 -3.1936 -0.3952 -2.6173 -0.3801 -2.1533 -0.3677 -1.7740 -0.3572 -1.4598 -0.3480 -1.1967 -0.3399 -0.9743 -0.3326 -0.7850 -0.3260 -0.6226 -0.3201 -0.4826 -0.3147 -0.3611 -0.3099 -0.2553 -0.3055 -0.1627 -0.3015 -0.0814 -0.2980 -0.0096 -0.2948 0.0540 -0.2919 0.1105 -0.2893 0.1610 -0.2871 0.2062 -0.2851 0.2469 -0.2833 0.2836 -0.2818 0.3170 -0.2806 0.3474 -0.2795 0.3753 -0.2786 0.4010 -0.2778 0.4249 -0.2772 0.4472 -0.2767 0.4682 -0.2763 0.4882 -0.2760 0.5075 -0.2758 0.5264 -0.2756 0.5454 -0.2755 0.5647 -0.2754 0.5858 -0.2754 0.6098 -0.2753 0.6354 -0.2753 0.7227 -0.2753 -0.1621 -0.2753 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -40.500 0.375 -0.580 0.091 1.000 0.157 0.0000 -0.6329 Cpi Cpv ----------------- -0.1775 -0.2769 -0.0683 -0.2769 0.6219 -0.2763 0.6086 -0.2751 0.5941 -0.2733 0.5837 -0.2705 0.5751 -0.2665 0.5683 -0.2607 0.5634 -0.2529 0.5600 -0.2429 0.5582 -0.2306 0.5577 -0.2161 0.5586 -0.1998 0.5608 -0.1818 0.5643 -0.1625 0.5690 -0.1422 0.5750 -0.1210 0.5823 -0.0993 0.5911 -0.0770 0.6013 -0.0541 0.6131 -0.0306 0.6266 -0.0063 0.6419 0.0189 0.6592 0.0454 0.6785 0.0732 0.6998 0.1028 0.7234 0.1345 0.7491 0.1684 0.7768 0.2050 0.8063 0.2445 0.8373 0.2870 0.8691 0.3328 0.9010 0.3819 0.9317 0.4343 0.9597 0.4898 0.9824 0.5482 0.9970 0.6089 0.9989 0.6712 0.9821 0.7341 0.9380 0.7965 0.8541 0.8559 0.7117 0.9108 0.4823 0.9564 0.1201 0.9890 -0.4511 0.9998 -1.3657 0.9779 -2.8754 0.9030 -5.4878 0.7440 -10.3229 0.4460 -20.0513 -0.0565 -41.5218 -0.6329 -82.6086 -0.5378 -87.6215 -0.4926 -52.4096 -0.4909 -31.2170 -0.4919 -20.2180 -0.4903 -14.0323 -0.4868 -10.2548 -0.4829 -7.7795 -0.4792 -6.0639 -0.4760 -4.8209 -0.4654 -3.8879 -0.4220 -3.1673 -0.4006 -2.5977 -0.3847 -2.1389 -0.3717 -1.7636 -0.3607 -1.4525 -0.3512 -1.1918 -0.3427 -0.9715 -0.3352 -0.7837 -0.3285 -0.6226 -0.3224 -0.4835 -0.3169 -0.3629 -0.3120 -0.2578 -0.3075 -0.1658 -0.3035 -0.0849 -0.2998 -0.0135 -0.2966 0.0497 -0.2937 0.1060 -0.2911 0.1562 -0.2888 0.2012 -0.2868 0.2417 -0.2850 0.2783 -0.2835 0.3116 -0.2822 0.3419 -0.2811 0.3697 -0.2802 0.3953 -0.2795 0.4191 -0.2788 0.4414 -0.2783 0.4624 -0.2779 0.4824 -0.2776 0.5018 -0.2774 0.5208 -0.2772 0.5398 -0.2771 0.5593 -0.2770 0.5806 -0.2770 0.6048 -0.2769 0.6307 -0.2769 0.7191 -0.2769 -0.1775 -0.2769 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -40.000 0.378 -0.582 0.088 1.000 0.159 0.0000 -0.6343 Cpi Cpv ----------------- -0.1927 -0.2792 -0.0822 -0.2792 0.6169 -0.2786 0.6034 -0.2774 0.5887 -0.2757 0.5781 -0.2730 0.5692 -0.2690 0.5623 -0.2634 0.5571 -0.2558 0.5535 -0.2461 0.5515 -0.2341 0.5508 -0.2200 0.5514 -0.2040 0.5534 -0.1864 0.5566 -0.1675 0.5611 -0.1476 0.5668 -0.1269 0.5739 -0.1056 0.5823 -0.0838 0.5923 -0.0613 0.6038 -0.0383 0.6171 -0.0145 0.6321 0.0103 0.6491 0.0362 0.6682 0.0636 0.6895 0.0927 0.7129 0.1238 0.7386 0.1573 0.7663 0.1935 0.7961 0.2325 0.8274 0.2747 0.8597 0.3202 0.8924 0.3690 0.9241 0.4213 0.9534 0.4768 0.9780 0.5352 0.9949 0.5962 0.9998 0.6590 0.9868 0.7226 0.9476 0.7858 0.8700 0.8467 0.7358 0.9029 0.5172 0.9510 0.1697 0.9857 -0.3814 1.0000 -1.2671 0.9816 -2.7334 0.9128 -5.2770 0.7584 -9.9941 0.4674 -19.5020 -0.0349 -40.5213 -0.6343 -80.8390 -0.5571 -85.9329 -0.5081 -51.4908 -0.5052 -30.7138 -0.5058 -19.9172 -0.5040 -13.8392 -0.5004 -10.1242 -0.4963 -7.6877 -0.4926 -5.9977 -0.4893 -4.7723 -0.4818 -3.8519 -0.4317 -3.1404 -0.4086 -2.5777 -0.3914 -2.1241 -0.3775 -1.7528 -0.3658 -1.4448 -0.3557 -1.1867 -0.3469 -0.9683 -0.3390 -0.7821 -0.3320 -0.6223 -0.3257 -0.4843 -0.3201 -0.3645 -0.3150 -0.2601 -0.3104 -0.1687 -0.3062 -0.0883 -0.3025 -0.0173 -0.2992 0.0456 -0.2962 0.1015 -0.2935 0.1515 -0.2912 0.1963 -0.2892 0.2366 -0.2875 0.2731 -0.2859 0.3062 -0.2846 0.3364 -0.2835 0.3642 -0.2826 0.3897 -0.2818 0.4135 -0.2811 0.4358 -0.2806 0.4567 -0.2802 0.4767 -0.2799 0.4961 -0.2797 0.5152 -0.2795 0.5343 -0.2794 0.5539 -0.2793 0.5754 -0.2792 0.5998 -0.2792 0.6260 -0.2792 0.7155 -0.2792 -0.1927 -0.2792 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -39.500 0.384 -0.587 0.086 1.000 0.161 0.0000 -0.6390 Cpi Cpv ----------------- -0.2079 -0.2828 -0.0960 -0.2828 0.6120 -0.2822 0.5983 -0.2811 0.5833 -0.2793 0.5725 -0.2767 0.5634 -0.2729 0.5562 -0.2674 0.5509 -0.2600 0.5470 -0.2504 0.5448 -0.2387 0.5438 -0.2249 0.5443 -0.2092 0.5460 -0.1920 0.5489 -0.1734 0.5531 -0.1539 0.5586 -0.1336 0.5654 -0.1127 0.5736 -0.0912 0.5832 -0.0692 0.5945 -0.0466 0.6074 -0.0232 0.6223 0.0012 0.6390 0.0267 0.6579 0.0536 0.6790 0.0823 0.7023 0.1130 0.7279 0.1460 0.7557 0.1818 0.7856 0.2204 0.8172 0.2623 0.8501 0.3075 0.8834 0.3561 0.9161 0.4082 0.9467 0.4637 0.9731 0.5223 0.9922 0.5835 1.0000 0.6468 0.9908 0.7111 0.9564 0.7751 0.8850 0.8374 0.7589 0.8950 0.5511 0.9452 0.2179 0.9823 -0.3131 0.9998 -1.1702 0.9852 -2.5936 0.9210 -5.0687 0.7720 -9.6685 0.4863 -18.9569 -0.0153 -39.5263 -0.6390 -79.0760 -0.5827 -84.2475 -0.5293 -50.5720 -0.5253 -30.2097 -0.5254 -19.6155 -0.5233 -13.6451 -0.5196 -9.9926 -0.5154 -7.5951 -0.5115 -5.9308 -0.5081 -4.7231 -0.5029 -3.8153 -0.4459 -3.1130 -0.4204 -2.5572 -0.4015 -2.1089 -0.3864 -1.7416 -0.3737 -1.4368 -0.3628 -1.1812 -0.3533 -0.9648 -0.3450 -0.7802 -0.3375 -0.6217 -0.3309 -0.4848 -0.3250 -0.3659 -0.3197 -0.2623 -0.3149 -0.1714 -0.3106 -0.0915 -0.3067 -0.0210 -0.3033 0.0416 -0.3002 0.0972 -0.2976 0.1469 -0.2952 0.1915 -0.2931 0.2317 -0.2913 0.2680 -0.2897 0.3009 -0.2884 0.3310 -0.2872 0.3587 -0.2862 0.3842 -0.2854 0.4079 -0.2848 0.4301 -0.2843 0.4511 -0.2838 0.4711 -0.2835 0.4905 -0.2833 0.5096 -0.2831 0.5288 -0.2830 0.5485 -0.2829 0.5702 -0.2828 0.5948 -0.2828 0.6213 -0.2828 0.7119 -0.2828 -0.2079 -0.2828 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -34.500 0.355 -0.572 0.062 1.000 0.203 0.0000 -0.6749 Cpi Cpv ----------------- -0.3541 -0.2994 -0.2290 -0.2993 0.5647 -0.2989 0.5488 -0.2981 0.5314 -0.2969 0.5183 -0.2950 0.5070 -0.2922 0.4976 -0.2883 0.4899 -0.2829 0.4838 -0.2759 0.4791 -0.2672 0.4757 -0.2569 0.4735 -0.2452 0.4725 -0.2322 0.4727 -0.2181 0.4739 -0.2033 0.4763 -0.1877 0.4800 -0.1717 0.4849 -0.1553 0.4912 -0.1384 0.4990 -0.1209 0.5086 -0.1029 0.5200 -0.0840 0.5335 -0.0641 0.5493 -0.0428 0.5675 -0.0199 0.5885 0.0051 0.6122 0.0325 0.6390 0.0626 0.6688 0.0959 0.7015 0.1327 0.7371 0.1733 0.7752 0.2180 0.8152 0.2670 0.8561 0.3203 0.8966 0.3780 0.9347 0.4398 0.9677 0.5054 0.9914 0.5743 0.9999 0.6457 0.9848 0.7181 0.9328 0.7903 0.8238 0.8588 0.6251 0.9215 0.2817 0.9703 -0.3045 0.9982 -1.3188 0.9873 -3.1393 0.9102 -6.6096 0.7082 -13.7716 0.2886 -29.9544 -0.4277 -61.9256 -0.6749 -67.6778 -0.5754 -41.4485 -0.5534 -25.1574 -0.5482 -16.5621 -0.5434 -11.6627 -0.5381 -8.6353 -0.5329 -6.6296 -0.5283 -5.2250 -0.5244 -4.1971 -0.5211 -3.4182 -0.5183 -2.8110 -0.4700 -2.3267 -0.4421 -1.9333 -0.4223 -1.6088 -0.4065 -1.3377 -0.3934 -1.1089 -0.3821 -0.9140 -0.3721 -0.7469 -0.3633 -0.6027 -0.3556 -0.4776 -0.3486 -0.3684 -0.3424 -0.2729 -0.3368 -0.1888 -0.3317 -0.1147 -0.3272 -0.0490 -0.3232 0.0094 -0.3197 0.0614 -0.3165 0.1081 -0.3137 0.1500 -0.3112 0.1878 -0.3091 0.2221 -0.3073 0.2533 -0.3058 0.2820 -0.3044 0.3084 -0.3033 0.3328 -0.3024 0.3557 -0.3017 0.3774 -0.3010 0.3980 -0.3006 0.4178 -0.3002 0.4373 -0.2999 0.4568 -0.2997 0.4766 -0.2996 0.4973 -0.2995 0.5204 -0.2994 0.5471 -0.2994 0.5761 -0.2994 0.6773 -0.2994 -0.3541 -0.2994 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -34.000 0.349 -0.567 0.060 1.000 0.210 0.0000 -0.6753 Cpi Cpv ----------------- -0.3681 -0.3006 -0.2417 -0.3006 0.5601 -0.3002 0.5441 -0.2994 0.5264 -0.2982 0.5132 -0.2964 0.5016 -0.2937 0.4919 -0.2899 0.4841 -0.2847 0.4777 -0.2780 0.4727 -0.2696 0.4691 -0.2597 0.4666 -0.2483 0.4653 -0.2358 0.4652 -0.2222 0.4661 -0.2078 0.4681 -0.1928 0.4714 -0.1773 0.4760 -0.1614 0.4819 -0.1450 0.4893 -0.1282 0.4985 -0.1107 0.5095 -0.0924 0.5226 -0.0731 0.5380 -0.0525 0.5558 -0.0301 0.5764 -0.0058 0.5999 0.0209 0.6264 0.0504 0.6560 0.0831 0.6887 0.1192 0.7243 0.1593 0.7626 0.2034 0.8031 0.2519 0.8447 0.3049 0.8863 0.3623 0.9260 0.4240 0.9610 0.4896 0.9875 0.5588 0.9998 0.6306 0.9896 0.7039 0.9443 0.7773 0.8443 0.8474 0.6580 0.9124 0.3320 0.9643 -0.2288 0.9965 -1.2046 0.9912 -2.9629 0.9216 -6.3255 0.7298 -13.2831 0.3223 -29.0414 -0.3923 -60.2700 -0.6753 -66.0603 -0.5707 -40.5487 -0.5463 -24.6543 -0.5405 -16.2553 -0.5354 -11.4616 -0.5300 -8.4963 -0.5248 -6.5297 -0.5201 -5.1512 -0.5162 -4.1416 -0.5129 -3.3757 -0.5100 -2.7782 -0.4747 -2.3013 -0.4448 -1.9135 -0.4246 -1.5935 -0.4087 -1.3259 -0.3955 -1.0999 -0.3842 -0.9074 -0.3742 -0.7422 -0.3654 -0.5995 -0.3575 -0.4756 -0.3505 -0.3675 -0.3442 -0.2729 -0.3385 -0.1896 -0.3335 -0.1161 -0.3289 -0.0510 -0.3249 0.0069 -0.3213 0.0586 -0.3181 0.1049 -0.3152 0.1464 -0.3127 0.1840 -0.3106 0.2181 -0.3087 0.2491 -0.3071 0.2775 -0.3058 0.3038 -0.3046 0.3282 -0.3037 0.3509 -0.3029 0.3725 -0.3023 0.3930 -0.3018 0.4128 -0.3015 0.4323 -0.3012 0.4518 -0.3010 0.4717 -0.3008 0.4925 -0.3007 0.5157 -0.3007 0.5426 -0.3006 0.5718 -0.3006 0.6740 -0.3006 -0.3681 -0.3006 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -33.500 0.346 -0.565 0.057 1.000 0.218 0.0000 -0.6863 Cpi Cpv ----------------- -0.3819 -0.3030 -0.2543 -0.3030 0.5557 -0.3026 0.5394 -0.3018 0.5215 -0.3007 0.5080 -0.2989 0.4962 -0.2964 0.4863 -0.2927 0.4782 -0.2876 0.4716 -0.2811 0.4664 -0.2730 0.4625 -0.2634 0.4597 -0.2524 0.4581 -0.2402 0.4577 -0.2270 0.4583 -0.2130 0.4600 -0.1985 0.4629 -0.1834 0.4671 -0.1680 0.4726 -0.1521 0.4796 -0.1358 0.4884 -0.1188 0.4990 -0.1011 0.5116 -0.0823 0.5266 -0.0622 0.5440 -0.0405 0.5642 -0.0168 0.5874 0.0093 0.6136 0.0382 0.6430 0.0703 0.6756 0.1059 0.7113 0.1454 0.7498 0.1891 0.7906 0.2371 0.8329 0.2897 0.8756 0.3468 0.9167 0.4084 0.9537 0.4741 0.9829 0.5435 0.9989 0.6159 0.9936 0.6899 0.9548 0.7645 0.8636 0.8362 0.6895 0.9034 0.3806 0.9582 -0.1552 0.9942 -1.0929 0.9942 -2.7899 0.9315 -6.0457 0.7487 -12.8007 0.3513 -28.1375 -0.3643 -58.6273 -0.6863 -64.4521 -0.5757 -39.6522 -0.5485 -24.1523 -0.5420 -15.9485 -0.5366 -11.2603 -0.5311 -8.3569 -0.5258 -6.4294 -0.5211 -5.0770 -0.5170 -4.0855 -0.5137 -3.3328 -0.5108 -2.7450 -0.4851 -2.2755 -0.4514 -1.8934 -0.4302 -1.5778 -0.4137 -1.3138 -0.4000 -1.0907 -0.3884 -0.9005 -0.3782 -0.7371 -0.3691 -0.5960 -0.3611 -0.4734 -0.3539 -0.3664 -0.3475 -0.2727 -0.3417 -0.1902 -0.3365 -0.1173 -0.3319 -0.0528 -0.3277 0.0047 -0.3240 0.0559 -0.3208 0.1018 -0.3179 0.1431 -0.3154 0.1803 -0.3132 0.2141 -0.3112 0.2450 -0.3096 0.2732 -0.3082 0.2993 -0.3071 0.3235 -0.3061 0.3462 -0.3054 0.3677 -0.3047 0.3881 -0.3042 0.4079 -0.3039 0.4274 -0.3036 0.4469 -0.3034 0.4668 -0.3032 0.4877 -0.3031 0.5110 -0.3031 0.5381 -0.3030 0.5676 -0.3030 0.6707 -0.3030 -0.3819 -0.3030 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -33.000 0.346 -0.564 0.055 1.000 0.225 0.0000 -0.7050 Cpi Cpv ----------------- -0.3955 -0.3062 -0.2667 -0.3061 0.5512 -0.3058 0.5347 -0.3050 0.5166 -0.3039 0.5029 -0.3022 0.4909 -0.2997 0.4808 -0.2961 0.4724 -0.2913 0.4656 -0.2849 0.4601 -0.2771 0.4559 -0.2677 0.4529 -0.2570 0.4510 -0.2452 0.4502 -0.2323 0.4505 -0.2188 0.4518 -0.2046 0.4544 -0.1900 0.4582 -0.1749 0.4633 -0.1595 0.4699 -0.1436 0.4782 -0.1271 0.4884 -0.1099 0.5006 -0.0917 0.5151 -0.0721 0.5322 -0.0509 0.5520 -0.0278 0.5747 -0.0022 0.6006 0.0261 0.6298 0.0576 0.6622 0.0926 0.6979 0.1316 0.7366 0.1748 0.7778 0.2224 0.8207 0.2747 0.8643 0.3316 0.9068 0.3931 0.9458 0.4588 0.9777 0.5285 0.9972 0.6013 0.9966 0.6761 0.9642 0.7518 0.8817 0.8250 0.7195 0.8943 0.4275 0.9518 -0.0837 0.9916 -0.9838 0.9964 -2.6201 0.9401 -5.7702 0.7657 -12.3245 0.3770 -27.2430 -0.3414 -56.9980 -0.7050 -62.8535 -0.5877 -38.7594 -0.5574 -23.6515 -0.5501 -15.6420 -0.5444 -11.0587 -0.5387 -8.2171 -0.5333 -6.3286 -0.5285 -5.0022 -0.5244 -4.0289 -0.5209 -3.2894 -0.5180 -2.7113 -0.5005 -2.2492 -0.4607 -1.8729 -0.4379 -1.5618 -0.4204 -1.3014 -0.4061 -1.0811 -0.3940 -0.8933 -0.3834 -0.7318 -0.3740 -0.5923 -0.3657 -0.4710 -0.3583 -0.3651 -0.3517 -0.2723 -0.3457 -0.1906 -0.3404 -0.1184 -0.3357 -0.0544 -0.3314 0.0025 -0.3276 0.0533 -0.3243 0.0989 -0.3214 0.1398 -0.3188 0.1768 -0.3165 0.2103 -0.3146 0.2410 -0.3129 0.2690 -0.3115 0.2950 -0.3103 0.3190 -0.3094 0.3416 -0.3086 0.3630 -0.3079 0.3833 -0.3074 0.4031 -0.3070 0.4225 -0.3067 0.4420 -0.3065 0.4620 -0.3064 0.4829 -0.3063 0.5064 -0.3062 0.5337 -0.3062 0.5634 -0.3062 0.6675 -0.3062 -0.3955 -0.3062 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -32.500 0.350 -0.568 0.054 1.000 0.231 0.0000 -0.7359 Cpi Cpv ----------------- -0.4091 -0.3113 -0.2790 -0.3113 0.5468 -0.3109 0.5301 -0.3102 0.5118 -0.3091 0.4979 -0.3075 0.4856 -0.3050 0.4753 -0.3015 0.4667 -0.2968 0.4596 -0.2906 0.4539 -0.2829 0.4494 -0.2737 0.4461 -0.2633 0.4439 -0.2517 0.4428 -0.2391 0.4427 -0.2258 0.4437 -0.2120 0.4459 -0.1976 0.4493 -0.1829 0.4540 -0.1679 0.4602 -0.1523 0.4681 -0.1363 0.4778 -0.1194 0.4895 -0.1016 0.5036 -0.0825 0.5202 -0.0618 0.5396 -0.0391 0.5620 -0.0141 0.5875 0.0137 0.6164 0.0447 0.6487 0.0793 0.6843 0.1178 0.7231 0.1606 0.7646 0.2079 0.8081 0.2599 0.8526 0.3166 0.8965 0.3780 0.9373 0.4438 0.9717 0.5137 0.9946 0.5870 0.9986 0.6626 0.9725 0.7394 0.8985 0.8140 0.7480 0.8854 0.4726 0.9455 -0.0144 0.9888 -0.8774 0.9980 -2.4537 0.9474 -5.4993 0.7800 -11.8547 0.3978 -26.3583 -0.3268 -55.3825 -0.7359 -61.2651 -0.6108 -37.8706 -0.5769 -23.1519 -0.5687 -15.3357 -0.5627 -10.8570 -0.5568 -8.0769 -0.5512 -6.2274 -0.5463 -4.9271 -0.5421 -3.9719 -0.5385 -3.2456 -0.5355 -2.6773 -0.5251 -2.2226 -0.4757 -1.8521 -0.4505 -1.5455 -0.4315 -1.2886 -0.4161 -1.0713 -0.4030 -0.8858 -0.3917 -0.7263 -0.3818 -0.5883 -0.3730 -0.4684 -0.3653 -0.3636 -0.3583 -0.2717 -0.3521 -0.1908 -0.3466 -0.1193 -0.3417 -0.0559 -0.3373 0.0006 -0.3334 0.0509 -0.3299 0.0961 -0.3268 0.1367 -0.3242 0.1734 -0.3219 0.2067 -0.3199 0.2371 -0.3182 0.2649 -0.3168 0.2907 -0.3156 0.3146 -0.3146 0.3370 -0.3138 0.3583 -0.3131 0.3786 -0.3126 0.3983 -0.3122 0.4177 -0.3119 0.4372 -0.3117 0.4572 -0.3115 0.4782 -0.3114 0.5018 -0.3113 0.5293 -0.3113 0.5592 -0.3113 0.6643 -0.3113 -0.4091 -0.3113 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -32.000 0.361 -0.579 0.053 1.000 0.234 0.0000 -0.7854 Cpi Cpv ----------------- -0.4225 -0.3211 -0.2912 -0.3210 0.5425 -0.3207 0.5256 -0.3200 0.5070 -0.3189 0.4929 -0.3173 0.4804 -0.3149 0.4698 -0.3115 0.4610 -0.3067 0.4536 -0.3006 0.4477 -0.2929 0.4429 -0.2839 0.4393 -0.2735 0.4368 -0.2620 0.4354 -0.2495 0.4350 -0.2363 0.4356 -0.2225 0.4374 -0.2083 0.4404 -0.1938 0.4447 -0.1788 0.4505 -0.1635 0.4579 -0.1476 0.4671 -0.1310 0.4784 -0.1134 0.4920 -0.0946 0.5082 -0.0742 0.5271 -0.0518 0.5491 -0.0271 0.5743 0.0004 0.6029 0.0311 0.6350 0.0653 0.6705 0.1036 0.7093 0.1461 0.7511 0.1931 0.7951 0.2450 0.8405 0.3016 0.8856 0.3631 0.9282 0.4291 0.9650 0.4994 0.9912 0.5733 0.9998 0.6496 0.9797 0.7276 0.9140 0.8037 0.7750 0.8770 0.5159 0.9394 0.0529 0.9859 -0.7736 0.9990 -2.2907 0.9530 -5.2329 0.7908 -11.3914 0.4116 -25.4835 -0.3248 -53.7814 -0.7854 -59.6873 -0.6507 -36.9859 -0.6126 -22.6539 -0.6035 -15.0299 -0.5971 -10.6552 -0.5909 -7.9365 -0.5850 -6.1258 -0.5799 -4.8515 -0.5756 -3.9145 -0.5719 -3.2013 -0.5687 -2.6428 -0.5632 -2.1956 -0.5023 -1.8308 -0.4735 -1.5288 -0.4519 -1.2756 -0.4345 -1.0612 -0.4198 -0.8780 -0.4073 -0.7205 -0.3964 -0.5841 -0.3868 -0.4655 -0.3784 -0.3619 -0.3709 -0.2709 -0.3643 -0.1908 -0.3583 -0.1200 -0.3530 -0.0572 -0.3483 -0.0013 -0.3443 0.0486 -0.3406 0.0934 -0.3375 0.1337 -0.3347 0.1701 -0.3323 0.2031 -0.3302 0.2333 -0.3284 0.2609 -0.3269 0.2865 -0.3256 0.3103 -0.3245 0.3326 -0.3237 0.3537 -0.3230 0.3740 -0.3224 0.3936 -0.3220 0.4130 -0.3217 0.4325 -0.3215 0.4525 -0.3213 0.4736 -0.3212 0.4973 -0.3211 0.5249 -0.3211 0.5551 -0.3211 0.6611 -0.3211 -0.4225 -0.3211 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -28.000 0.326 -0.552 0.037 1.000 0.295 0.0000 -0.8972 Cpi Cpv ----------------- -0.5236 -0.3459 -0.3832 -0.3459 0.5096 -0.3456 0.4912 -0.3451 0.4707 -0.3443 0.4549 -0.3432 0.4407 -0.3413 0.4282 -0.3387 0.4175 -0.3351 0.4081 -0.3305 0.4001 -0.3246 0.3931 -0.3177 0.3871 -0.3097 0.3820 -0.3008 0.3778 -0.2912 0.3745 -0.2810 0.3721 -0.2705 0.3706 -0.2596 0.3702 -0.2486 0.3709 -0.2373 0.3728 -0.2258 0.3763 -0.2139 0.3814 -0.2014 0.3885 -0.1882 0.3978 -0.1739 0.4096 -0.1582 0.4243 -0.1408 0.4422 -0.1211 0.4635 -0.0987 0.4887 -0.0733 0.5179 -0.0442 0.5513 -0.0110 0.5891 0.0267 0.6312 0.0693 0.6774 0.1172 0.7272 0.1706 0.7796 0.2297 0.8334 0.2945 0.8864 0.3649 0.9352 0.4407 0.9750 0.5212 0.9980 0.6055 0.9919 0.6927 0.9365 0.7789 0.7972 0.8635 0.5111 0.9357 -0.0426 0.9885 -1.1148 0.9948 -3.2755 0.9083 -7.9358 0.6160 -18.8760 -0.0776 -41.5467 -0.8972 -47.5052 -0.7137 -30.0915 -0.6347 -18.7405 -0.6169 -12.6076 -0.6080 -9.0449 -0.6008 -6.8073 -0.5943 -5.3027 -0.5887 -4.2342 -0.5838 -3.4419 -0.5796 -2.8339 -0.5761 -2.3541 -0.5731 -1.9670 -0.5704 -1.6491 -0.5400 -1.3841 -0.5046 -1.1605 -0.4813 -0.9701 -0.4630 -0.8065 -0.4478 -0.6652 -0.4348 -0.5423 -0.4234 -0.4349 -0.4134 -0.3407 -0.4046 -0.2578 -0.3968 -0.1845 -0.3898 -0.1196 -0.3836 -0.0619 -0.3781 -0.0104 -0.3733 0.0356 -0.3690 0.0770 -0.3652 0.1142 -0.3619 0.1480 -0.3590 0.1787 -0.3566 0.2068 -0.3544 0.2326 -0.3526 0.2566 -0.3511 0.2790 -0.3499 0.3001 -0.3489 0.3203 -0.3481 0.3397 -0.3475 0.3588 -0.3470 0.3778 -0.3466 0.3972 -0.3464 0.4174 -0.3462 0.4388 -0.3460 0.4633 -0.3460 0.4922 -0.3459 0.5240 -0.3459 0.6372 -0.3459 -0.5236 -0.3459 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -27.500 0.327 -0.555 0.036 1.000 0.306 0.0000 -0.9208 Cpi Cpv ----------------- -0.5354 -0.3544 -0.3940 -0.3544 0.5058 -0.3541 0.4871 -0.3537 0.4665 -0.3529 0.4504 -0.3517 0.4360 -0.3500 0.4233 -0.3474 0.4124 -0.3439 0.4027 -0.3393 0.3944 -0.3335 0.3871 -0.3267 0.3808 -0.3188 0.3754 -0.3101 0.3709 -0.3006 0.3672 -0.2907 0.3644 -0.2803 0.3625 -0.2696 0.3615 -0.2588 0.3617 -0.2478 0.3632 -0.2365 0.3661 -0.2249 0.3706 -0.2128 0.3772 -0.1999 0.3859 -0.1860 0.3971 -0.1707 0.4111 -0.1537 0.4284 -0.1345 0.4491 -0.1126 0.4737 -0.0876 0.5024 -0.0590 0.5354 -0.0263 0.5729 0.0109 0.6148 0.0530 0.6610 0.1005 0.7111 0.1536 0.7641 0.2124 0.8189 0.2771 0.8735 0.3476 0.9246 0.4235 0.9677 0.5045 0.9954 0.5895 0.9958 0.6779 0.9498 0.7657 0.8240 0.8526 0.5582 0.9278 0.0359 0.9850 -0.9845 0.9969 -3.0537 0.9181 -7.5372 0.6351 -18.1026 -0.0555 -40.0961 -0.9208 -46.0444 -0.7379 -29.2566 -0.6522 -18.2625 -0.6327 -12.3093 -0.6233 -8.8451 -0.6158 -6.6661 -0.6092 -5.1990 -0.6034 -4.1559 -0.5984 -3.3815 -0.5942 -2.7865 -0.5906 -2.3165 -0.5874 -1.9370 -0.5847 -1.6249 -0.5676 -1.3646 -0.5231 -1.1448 -0.4973 -0.9575 -0.4775 -0.7965 -0.4612 -0.6572 -0.4474 -0.5360 -0.4353 -0.4301 -0.4248 -0.3371 -0.4155 -0.2553 -0.4073 -0.1829 -0.4000 -0.1188 -0.3936 -0.0618 -0.3879 -0.0109 -0.3828 0.0347 -0.3783 0.0756 -0.3744 0.1124 -0.3710 0.1458 -0.3680 0.1762 -0.3654 0.2040 -0.3632 0.2295 -0.3614 0.2533 -0.3598 0.2755 -0.3586 0.2964 -0.3575 0.3165 -0.3567 0.3358 -0.3560 0.3548 -0.3555 0.3738 -0.3551 0.3931 -0.3549 0.4133 -0.3547 0.4348 -0.3545 0.4594 -0.3545 0.4884 -0.3544 0.5203 -0.3544 0.6344 -0.3544 -0.5354 -0.3544 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -27.000 0.340 -0.574 0.037 1.000 0.313 0.0000 -0.9786 Cpi Cpv ----------------- -0.5471 -0.3744 -0.4046 -0.3743 0.5020 -0.3741 0.4832 -0.3736 0.4623 -0.3729 0.4460 -0.3717 0.4314 -0.3699 0.4185 -0.3673 0.4073 -0.3637 0.3974 -0.3590 0.3887 -0.3531 0.3812 -0.3461 0.3746 -0.3380 0.3688 -0.3290 0.3640 -0.3194 0.3599 -0.3091 0.3567 -0.2985 0.3543 -0.2876 0.3529 -0.2766 0.3526 -0.2653 0.3536 -0.2539 0.3559 -0.2421 0.3599 -0.2299 0.3658 -0.2169 0.3739 -0.2030 0.3845 -0.1877 0.3979 -0.1707 0.4145 -0.1515 0.4346 -0.1297 0.4586 -0.1048 0.4868 -0.0763 0.5193 -0.0437 0.5565 -0.0066 0.5982 0.0355 0.6443 0.0830 0.6945 0.1361 0.7481 0.1950 0.8039 0.2600 0.8599 0.3308 0.9132 0.4073 0.9595 0.4890 0.9916 0.5751 0.9985 0.6648 0.9616 0.7542 0.8490 0.8434 0.6029 0.9213 0.1116 0.9820 -0.8580 0.9980 -2.8372 0.9237 -7.1464 0.6437 -17.3418 -0.0559 -38.6646 -0.9786 -44.5989 -0.7959 -28.4284 -0.7024 -17.7874 -0.6808 -12.0123 -0.6707 -8.6457 -0.6628 -6.5250 -0.6558 -5.0952 -0.6498 -4.0773 -0.6446 -3.3207 -0.6401 -2.7388 -0.6363 -2.2787 -0.6330 -1.9067 -0.6302 -1.6005 -0.6225 -1.3449 -0.5630 -1.1289 -0.5328 -0.9446 -0.5100 -0.7861 -0.4915 -0.6490 -0.4758 -0.5295 -0.4624 -0.4251 -0.4507 -0.3334 -0.4405 -0.2526 -0.4315 -0.1812 -0.4235 -0.1178 -0.4164 -0.0615 -0.4102 -0.0112 -0.4047 0.0338 -0.3999 0.0743 -0.3957 0.1107 -0.3920 0.1437 -0.3889 0.1738 -0.3862 0.2013 -0.3838 0.2266 -0.3819 0.2501 -0.3802 0.2721 -0.3788 0.2929 -0.3777 0.3128 -0.3768 0.3320 -0.3761 0.3509 -0.3756 0.3698 -0.3752 0.3891 -0.3749 0.4093 -0.3747 0.4308 -0.3745 0.4555 -0.3744 0.4847 -0.3744 0.5168 -0.3744 0.6316 -0.3744 -0.5471 -0.3744 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -26.500 0.366 -0.618 0.041 1.000 0.316 0.0000 -1.0840 Cpi Cpv ----------------- -0.5586 -0.4171 -0.4151 -0.4171 0.4983 -0.4169 0.4793 -0.4164 0.4581 -0.4157 0.4417 -0.4144 0.4268 -0.4125 0.4137 -0.4096 0.4022 -0.4056 0.3921 -0.4005 0.3832 -0.3940 0.3753 -0.3862 0.3684 -0.3774 0.3623 -0.3675 0.3571 -0.3568 0.3527 -0.3456 0.3490 -0.3340 0.3462 -0.3221 0.3444 -0.3100 0.3436 -0.2977 0.3440 -0.2853 0.3458 -0.2726 0.3492 -0.2594 0.3545 -0.2456 0.3619 -0.2308 0.3719 -0.2147 0.3846 -0.1969 0.4006 -0.1770 0.4201 -0.1545 0.4434 -0.1290 0.4710 -0.0998 0.5031 -0.0666 0.5398 -0.0289 0.5812 0.0138 0.6272 0.0620 0.6776 0.1158 0.7316 0.1755 0.7882 0.2414 0.8456 0.3132 0.9011 0.3909 0.9503 0.4739 0.9868 0.5615 0.9998 0.6530 0.9717 0.7445 0.8721 0.8361 0.6454 0.9166 0.1842 0.9800 -0.7355 0.9985 -2.6260 0.9248 -6.7635 0.6395 -16.5936 -0.0856 -37.2525 -1.0840 -43.1691 -0.8999 -27.6074 -0.7969 -17.3154 -0.7725 -11.7167 -0.7614 -8.4470 -0.7529 -6.3841 -0.7454 -4.9914 -0.7389 -3.9986 -0.7333 -3.2598 -0.7286 -2.6909 -0.7245 -2.2405 -0.7209 -1.8761 -0.7178 -1.5758 -0.7149 -1.3249 -0.6393 -1.1127 -0.6027 -0.9315 -0.5751 -0.7756 -0.5528 -0.6405 -0.5341 -0.5228 -0.5183 -0.4199 -0.5045 -0.3294 -0.4926 -0.2497 -0.4821 -0.1792 -0.4729 -0.1167 -0.4649 -0.0610 -0.4578 -0.0113 -0.4516 0.0331 -0.4462 0.0731 -0.4414 0.1091 -0.4372 0.1418 -0.4336 0.1715 -0.4305 0.1987 -0.4279 0.2238 -0.4257 0.2471 -0.4238 0.2688 -0.4222 0.2894 -0.4210 0.3092 -0.4199 0.3283 -0.4191 0.3471 -0.4185 0.3659 -0.4181 0.3852 -0.4177 0.4054 -0.4175 0.4269 -0.4173 0.4516 -0.4172 0.4810 -0.4172 0.5133 -0.4172 0.6289 -0.4171 -0.5586 -0.4171 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -26.000 0.321 -0.557 0.033 1.000 0.330 0.0000 -0.9542 Cpi Cpv ----------------- -0.5698 -0.3772 -0.4253 -0.3772 0.4946 -0.3770 0.4754 -0.3766 0.4541 -0.3759 0.4374 -0.3749 0.4223 -0.3732 0.4090 -0.3708 0.3973 -0.3675 0.3869 -0.3632 0.3777 -0.3578 0.3696 -0.3514 0.3623 -0.3440 0.3559 -0.3358 0.3503 -0.3269 0.3455 -0.3176 0.3414 -0.3079 0.3382 -0.2980 0.3359 -0.2879 0.3345 -0.2778 0.3344 -0.2674 0.3356 -0.2568 0.3384 -0.2458 0.3431 -0.2341 0.3499 -0.2214 0.3592 -0.2075 0.3713 -0.1920 0.3866 -0.1743 0.4054 -0.1540 0.4281 -0.1307 0.4551 -0.1038 0.4866 -0.0728 0.5228 -0.0373 0.5639 0.0033 0.6098 0.0493 0.6603 0.1012 0.7147 0.1590 0.7720 0.2231 0.8307 0.2933 0.8881 0.3696 0.9403 0.4517 0.9809 0.5387 0.9999 0.6301 0.9803 0.7225 0.8932 0.8160 0.6854 0.9002 0.2539 0.9704 -0.6169 1.0000 -2.4203 0.9454 -6.3887 0.6967 -15.8585 0.0248 -35.8602 -0.9542 -41.7555 -0.7999 -26.7936 -0.6949 -16.8467 -0.6690 -11.4226 -0.6577 -8.2489 -0.6493 -6.2435 -0.6422 -4.8875 -0.6360 -3.9197 -0.6307 -3.1986 -0.6261 -2.6427 -0.6222 -2.2021 -0.6189 -1.8452 -0.6160 -1.5509 -0.6134 -1.3047 -0.5737 -1.0962 -0.5393 -0.9182 -0.5154 -0.7648 -0.4965 -0.6318 -0.4807 -0.5159 -0.4671 -0.4145 -0.4552 -0.3253 -0.4448 -0.2467 -0.4357 -0.1771 -0.4276 -0.1153 -0.4205 -0.0604 -0.4141 -0.0113 -0.4085 0.0326 -0.4036 0.0721 -0.3993 0.1077 -0.3955 0.1400 -0.3922 0.1693 -0.3894 0.1963 -0.3870 0.2210 -0.3849 0.2441 -0.3832 0.2657 -0.3818 0.2861 -0.3807 0.3057 -0.3798 0.3247 -0.3791 0.3434 -0.3785 0.3621 -0.3781 0.3814 -0.3778 0.4015 -0.3776 0.4231 -0.3774 0.4479 -0.3773 0.4773 -0.3773 0.5098 -0.3773 0.6263 -0.3772 -0.5698 -0.3772 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -25.500 0.320 -0.558 0.032 1.000 0.344 0.0000 -0.9550 Cpi Cpv ----------------- -0.5809 -0.3873 -0.4354 -0.3873 0.4910 -0.3871 0.4716 -0.3867 0.4501 -0.3860 0.4332 -0.3850 0.4179 -0.3834 0.4043 -0.3810 0.3924 -0.3778 0.3817 -0.3735 0.3723 -0.3682 0.3639 -0.3619 0.3563 -0.3546 0.3496 -0.3465 0.3436 -0.3378 0.3384 -0.3286 0.3339 -0.3190 0.3302 -0.3093 0.3274 -0.2994 0.3256 -0.2895 0.3249 -0.2794 0.3255 -0.2690 0.3277 -0.2583 0.3318 -0.2469 0.3379 -0.2347 0.3465 -0.2211 0.3579 -0.2060 0.3725 -0.1888 0.3906 -0.1690 0.4126 -0.1462 0.4390 -0.1198 0.4699 -0.0894 0.5056 -0.0543 0.5464 -0.0143 0.5921 0.0313 0.6425 0.0827 0.6972 0.1402 0.7552 0.2041 0.8151 0.2742 0.8743 0.3507 0.9293 0.4330 0.9739 0.5208 0.9986 0.6127 0.9874 0.7078 0.9125 0.8016 0.7232 0.8910 0.3206 0.9629 -0.5022 0.9998 -2.2201 0.9519 -6.0221 0.7200 -15.1365 0.0532 -34.4883 -0.9550 -40.3585 -0.8207 -25.9874 -0.7090 -16.3813 -0.6806 -11.1300 -0.6685 -8.0515 -0.6598 -6.1031 -0.6524 -4.7837 -0.6461 -3.8408 -0.6406 -3.1373 -0.6360 -2.5943 -0.6320 -2.1634 -0.6286 -1.8141 -0.6256 -1.5257 -0.6230 -1.2842 -0.6004 -1.0795 -0.5583 -0.9046 -0.5322 -0.7537 -0.5119 -0.6229 -0.4952 -0.5088 -0.4809 -0.4089 -0.4685 -0.3210 -0.4576 -0.2434 -0.4481 -0.1748 -0.4396 -0.1138 -0.4322 -0.0596 -0.4256 -0.0111 -0.4198 0.0322 -0.4147 0.0712 -0.4102 0.1064 -0.4062 0.1383 -0.4028 0.1673 -0.3999 0.1939 -0.3974 0.2184 -0.3953 0.2413 -0.3935 0.2626 -0.3920 0.2829 -0.3909 0.3023 -0.3899 0.3212 -0.3892 0.3397 -0.3886 0.3584 -0.3882 0.3776 -0.3878 0.3977 -0.3876 0.4193 -0.3875 0.4442 -0.3874 0.4738 -0.3873 0.5064 -0.3873 0.6236 -0.3873 -0.5809 -0.3873 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -25.000 0.332 -0.583 0.034 1.000 0.354 0.0000 -1.0084 Cpi Cpv ----------------- -0.5918 -0.4169 -0.4453 -0.4169 0.4875 -0.4167 0.4679 -0.4163 0.4461 -0.4156 0.4291 -0.4145 0.4136 -0.4129 0.3998 -0.4104 0.3876 -0.4070 0.3767 -0.4025 0.3670 -0.3969 0.3582 -0.3902 0.3503 -0.3825 0.3433 -0.3739 0.3370 -0.3647 0.3313 -0.3550 0.3264 -0.3449 0.3223 -0.3347 0.3190 -0.3243 0.3166 -0.3138 0.3154 -0.3033 0.3154 -0.2925 0.3170 -0.2813 0.3204 -0.2696 0.3259 -0.2569 0.3338 -0.2431 0.3445 -0.2277 0.3583 -0.2103 0.3757 -0.1903 0.3971 -0.1673 0.4227 -0.1408 0.4530 -0.1102 0.4882 -0.0751 0.5286 -0.0348 0.5740 0.0109 0.6244 0.0625 0.6793 0.1203 0.7379 0.1846 0.7988 0.2553 0.8598 0.3324 0.9173 0.4156 0.9658 0.5045 0.9960 0.5978 0.9929 0.6948 0.9299 0.7906 0.7585 0.8831 0.3842 0.9582 -0.3915 0.9993 -2.0254 0.9560 -5.6638 0.7271 -14.4279 0.0524 -33.1370 -1.0084 -38.9784 -0.8899 -25.1890 -0.7693 -15.9195 -0.7378 -10.8392 -0.7245 -7.8549 -0.7152 -5.9629 -0.7074 -4.6800 -0.7007 -3.7617 -0.6949 -3.0758 -0.6900 -2.5457 -0.6858 -2.1245 -0.6822 -1.7827 -0.6791 -1.5002 -0.6763 -1.2634 -0.6661 -1.0626 -0.6086 -0.8907 -0.5780 -0.7425 -0.5547 -0.6138 -0.5357 -0.5015 -0.5195 -0.4030 -0.5057 -0.3164 -0.4936 -0.2400 -0.4830 -0.1723 -0.4738 -0.1122 -0.4656 -0.0586 -0.4584 -0.0108 -0.4520 0.0320 -0.4464 0.0705 -0.4415 0.1052 -0.4372 0.1367 -0.4336 0.1654 -0.4304 0.1917 -0.4278 0.2160 -0.4255 0.2385 -0.4236 0.2597 -0.4220 0.2797 -0.4208 0.2990 -0.4197 0.3177 -0.4189 0.3362 -0.4183 0.3548 -0.4178 0.3739 -0.4175 0.3941 -0.4172 0.4157 -0.4171 0.4406 -0.4170 0.4703 -0.4169 0.5031 -0.4169 0.6211 -0.4169 -0.5918 -0.4169 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -24.500 0.354 -0.634 0.039 1.000 0.358 0.0000 -1.1113 Cpi Cpv ----------------- -0.6025 -0.4642 -0.4550 -0.4642 0.4840 -0.4640 0.4643 -0.4636 0.4423 -0.4629 0.4250 -0.4618 0.4093 -0.4599 0.3953 -0.4572 0.3829 -0.4534 0.3717 -0.4483 0.3617 -0.4420 0.3527 -0.4345 0.3445 -0.4259 0.3370 -0.4163 0.3304 -0.4059 0.3243 -0.3950 0.3190 -0.3838 0.3144 -0.3723 0.3106 -0.3608 0.3077 -0.3491 0.3059 -0.3374 0.3054 -0.3255 0.3064 -0.3133 0.3091 -0.3005 0.3139 -0.2869 0.3211 -0.2721 0.3310 -0.2558 0.3441 -0.2375 0.3608 -0.2167 0.3814 -0.1929 0.4063 -0.1657 0.4360 -0.1344 0.4706 -0.0985 0.5105 -0.0575 0.5556 -0.0110 0.6058 0.0414 0.6609 0.1001 0.7200 0.1652 0.7819 0.2370 0.8445 0.3153 0.9045 0.3999 0.9566 0.4904 0.9922 0.5855 0.9968 0.6846 0.9454 0.7827 0.7915 0.8779 0.4448 0.9556 -0.2849 0.9991 -1.8364 0.9564 -5.3138 0.7223 -13.7329 0.0225 -31.8069 -1.1113 -37.6158 -1.0056 -24.3987 -0.8738 -15.4614 -0.8386 -10.5500 -0.8240 -7.6591 -0.8138 -5.8232 -0.8053 -4.5763 -0.7981 -3.6826 -0.7919 -3.0141 -0.7866 -2.4968 -0.7821 -2.0854 -0.7781 -1.7510 -0.7747 -1.4744 -0.7717 -1.2424 -0.7683 -1.0454 -0.6921 -0.8766 -0.6544 -0.7310 -0.6259 -0.6044 -0.6028 -0.4939 -0.5835 -0.3970 -0.5670 -0.3117 -0.5527 -0.2364 -0.5403 -0.1696 -0.5294 -0.1103 -0.5199 -0.0575 -0.5115 -0.0104 -0.5043 0.0319 -0.4979 0.0699 -0.4924 0.1042 -0.4875 0.1353 -0.4833 0.1636 -0.4797 0.1896 -0.4767 0.2136 -0.4741 0.2359 -0.4719 0.2568 -0.4701 0.2767 -0.4686 0.2958 -0.4674 0.3144 -0.4665 0.3327 -0.4658 0.3513 -0.4653 0.3703 -0.4649 0.3905 -0.4646 0.4121 -0.4644 0.4371 -0.4643 0.4669 -0.4642 0.4998 -0.4642 0.6186 -0.4642 -0.6025 -0.4642 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -24.000 0.318 -0.575 0.032 1.000 0.378 0.0000 -0.9782 Cpi Cpv ----------------- -0.6129 -0.4326 -0.4645 -0.4326 0.4806 -0.4324 0.4607 -0.4320 0.4385 -0.4314 0.4210 -0.4304 0.4051 -0.4288 0.3908 -0.4265 0.3782 -0.4232 0.3668 -0.4190 0.3565 -0.4136 0.3472 -0.4072 0.3387 -0.3999 0.3309 -0.3917 0.3238 -0.3830 0.3174 -0.3737 0.3116 -0.3642 0.3066 -0.3544 0.3023 -0.3447 0.2989 -0.3348 0.2965 -0.3249 0.2954 -0.3149 0.2957 -0.3045 0.2978 -0.2936 0.3019 -0.2819 0.3083 -0.2691 0.3175 -0.2547 0.3299 -0.2384 0.3458 -0.2196 0.3656 -0.1979 0.3898 -0.1727 0.4188 -0.1434 0.4528 -0.1095 0.4921 -0.0706 0.5368 -0.0261 0.5869 0.0245 0.6421 0.0813 0.7016 0.1448 0.7644 0.2150 0.8285 0.2920 0.8908 0.3756 0.9463 0.4654 0.9870 0.5603 0.9992 0.6601 0.9589 0.7595 0.8221 0.8584 0.5024 0.9416 -0.1823 0.9959 -1.6531 0.9719 -4.9724 0.7704 -13.0517 0.1274 -30.4984 -0.9782 -36.2711 -0.9183 -23.6167 -0.7832 -15.0071 -0.7454 -10.2627 -0.7302 -7.4642 -0.7200 -5.6838 -0.7117 -4.4727 -0.7047 -3.6034 -0.6988 -2.9523 -0.6937 -2.4478 -0.6893 -2.0460 -0.6856 -1.7192 -0.6823 -1.4485 -0.6795 -1.2211 -0.6769 -1.0279 -0.6428 -0.8623 -0.6044 -0.7192 -0.5784 -0.5948 -0.5579 -0.4862 -0.5409 -0.3908 -0.5262 -0.3068 -0.5135 -0.2326 -0.5023 -0.1668 -0.4926 -0.1083 -0.4840 -0.0563 -0.4764 -0.0097 -0.4697 0.0320 -0.4638 0.0695 -0.4587 0.1033 -0.4542 0.1340 -0.4503 0.1620 -0.4470 0.1877 -0.4441 0.2113 -0.4417 0.2334 -0.4397 0.2541 -0.4380 0.2738 -0.4366 0.2927 -0.4356 0.3111 -0.4347 0.3294 -0.4340 0.3478 -0.4336 0.3668 -0.4332 0.3869 -0.4329 0.4086 -0.4328 0.4336 -0.4327 0.4635 -0.4326 0.4966 -0.4326 0.6161 -0.4326 -0.6129 -0.4326 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -23.500 0.322 -0.593 0.034 1.000 0.395 0.0000 -1.0042 Cpi Cpv ----------------- -0.6231 -0.4556 -0.4739 -0.4556 0.4772 -0.4554 0.4572 -0.4551 0.4348 -0.4545 0.4171 -0.4535 0.4010 -0.4519 0.3865 -0.4494 0.3736 -0.4461 0.3619 -0.4417 0.3514 -0.4361 0.3418 -0.4295 0.3329 -0.4219 0.3248 -0.4135 0.3174 -0.4044 0.3105 -0.3949 0.3043 -0.3850 0.2988 -0.3750 0.2940 -0.3649 0.2901 -0.3548 0.2872 -0.3447 0.2854 -0.3344 0.2851 -0.3238 0.2865 -0.3128 0.2898 -0.3010 0.2956 -0.2881 0.3040 -0.2737 0.3155 -0.2574 0.3306 -0.2387 0.3497 -0.2171 0.3732 -0.1919 0.4014 -0.1628 0.4348 -0.1291 0.4735 -0.0903 0.5178 -0.0458 0.5676 0.0046 0.6228 0.0615 0.6826 0.1251 0.7462 0.1955 0.8116 0.2729 0.8761 0.3570 0.9350 0.4476 0.9806 0.5437 1.0000 0.6451 0.9705 0.7464 0.8503 0.8482 0.5569 0.9348 -0.0838 0.9940 -1.4754 0.9762 -4.6396 0.7814 -12.3846 0.1395 -29.2118 -1.0042 -34.9445 -0.9729 -22.8433 -0.8284 -14.5567 -0.7868 -9.9773 -0.7703 -7.2702 -0.7594 -5.5449 -0.7507 -4.3693 -0.7434 -3.5242 -0.7372 -2.8903 -0.7319 -2.3986 -0.7273 -2.0065 -0.7234 -1.6871 -0.7200 -1.4222 -0.7171 -1.1996 -0.7144 -1.0103 -0.7012 -0.8478 -0.6467 -0.7073 -0.6162 -0.5851 -0.5928 -0.4782 -0.5736 -0.3844 -0.5573 -0.3017 -0.5432 -0.2286 -0.5310 -0.1638 -0.5203 -0.1062 -0.5110 -0.0548 -0.5027 -0.0090 -0.4955 0.0322 -0.4891 0.0692 -0.4836 0.1026 -0.4788 0.1329 -0.4746 0.1605 -0.4710 0.1858 -0.4679 0.2092 -0.4653 0.2310 -0.4632 0.2515 -0.4614 0.2709 -0.4600 0.2897 -0.4588 0.3080 -0.4579 0.3261 -0.4572 0.3445 -0.4567 0.3634 -0.4563 0.3835 -0.4560 0.4051 -0.4558 0.4302 -0.4557 0.4603 -0.4557 0.4935 -0.4556 0.6137 -0.4556 -0.6231 -0.4556 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -23.000 0.336 -0.630 0.037 1.000 0.402 0.0000 -1.0690 Cpi Cpv ----------------- -0.6332 -0.4766 -0.4830 -0.4766 0.4740 -0.4765 0.4537 -0.4761 0.4311 -0.4755 0.4133 -0.4745 0.3969 -0.4728 0.3822 -0.4703 0.3691 -0.4668 0.3572 -0.4622 0.3464 -0.4563 0.3364 -0.4494 0.3273 -0.4414 0.3188 -0.4326 0.3110 -0.4230 0.3038 -0.4130 0.2971 -0.4027 0.2911 -0.3922 0.2858 -0.3817 0.2813 -0.3712 0.2778 -0.3607 0.2755 -0.3500 0.2745 -0.3392 0.2752 -0.3279 0.2778 -0.3159 0.2828 -0.3028 0.2904 -0.2883 0.3012 -0.2719 0.3155 -0.2532 0.3337 -0.2315 0.3564 -0.2064 0.3839 -0.1773 0.4165 -0.1437 0.4546 -0.1049 0.4984 -0.0605 0.5480 -0.0100 0.6030 0.0469 0.6631 0.1106 0.7273 0.1813 0.7940 0.2590 0.8606 0.3438 0.9226 0.4352 0.9729 0.5322 0.9992 0.6350 0.9802 0.7380 0.8760 0.8419 0.6083 0.9310 0.0105 0.9930 -1.3036 0.9776 -4.3155 0.7824 -11.7317 0.1278 -27.9474 -1.0690 -33.6367 -1.0620 -22.0786 -0.9066 -14.1105 -0.8608 -9.6940 -0.8429 -7.0772 -0.8312 -5.4064 -0.8219 -4.2660 -0.8141 -3.4450 -0.8075 -2.8283 -0.8019 -2.3492 -0.7971 -1.9667 -0.7929 -1.6547 -0.7893 -1.3958 -0.7861 -1.1779 -0.7833 -0.9924 -0.7805 -0.8330 -0.7041 -0.6951 -0.6661 -0.5751 -0.6372 -0.4700 -0.6137 -0.3778 -0.5941 -0.2964 -0.5774 -0.2244 -0.5630 -0.1606 -0.5505 -0.1039 -0.5396 -0.0533 -0.5300 -0.0080 -0.5217 0.0325 -0.5145 0.0690 -0.5082 0.1019 -0.5028 0.1318 -0.4981 0.1591 -0.4940 0.1841 -0.4906 0.2072 -0.4877 0.2287 -0.4852 0.2490 -0.4832 0.2682 -0.4816 0.2868 -0.4803 0.3050 -0.4792 0.3229 -0.4784 0.3412 -0.4778 0.3601 -0.4774 0.3801 -0.4771 0.4018 -0.4769 0.4269 -0.4767 0.4571 -0.4767 0.4904 -0.4766 0.6113 -0.4766 -0.6332 -0.4766 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -22.500 0.305 -0.580 0.031 1.000 0.429 0.0000 -0.9987 Cpi Cpv ----------------- -0.6430 -0.4634 -0.4919 -0.4634 0.4708 -0.4633 0.4504 -0.4630 0.4276 -0.4624 0.4095 -0.4615 0.3930 -0.4600 0.3781 -0.4578 0.3647 -0.4546 0.3525 -0.4505 0.3414 -0.4454 0.3312 -0.4392 0.3217 -0.4321 0.3129 -0.4242 0.3047 -0.4157 0.2971 -0.4068 0.2900 -0.3977 0.2835 -0.3884 0.2777 -0.3791 0.2727 -0.3699 0.2686 -0.3606 0.2656 -0.3513 0.2639 -0.3417 0.2639 -0.3318 0.2658 -0.3211 0.2700 -0.3095 0.2769 -0.2964 0.2868 -0.2815 0.3002 -0.2642 0.3177 -0.2441 0.3395 -0.2205 0.3661 -0.1930 0.3981 -0.1608 0.4355 -0.1236 0.4788 -0.0807 0.5279 -0.0317 0.5828 0.0238 0.6431 0.0862 0.7079 0.1557 0.7757 0.2325 0.8441 0.3165 0.9091 0.4075 0.9638 0.5047 0.9969 0.6082 0.9880 0.7128 0.8994 0.8201 0.6565 0.9144 0.1007 0.9863 -1.1376 0.9878 -4.0002 0.8218 -11.0932 0.2182 -26.7058 -0.9511 -32.3479 -0.9987 -21.3229 -0.8376 -13.6684 -0.7880 -9.4127 -0.7691 -6.8853 -0.7572 -5.2684 -0.7480 -4.1630 -0.7403 -3.3659 -0.7338 -2.7662 -0.7284 -2.2997 -0.7237 -1.9267 -0.7196 -1.6222 -0.7161 -1.3691 -0.7130 -1.1559 -0.7103 -0.9742 -0.7079 -0.8180 -0.6826 -0.6828 -0.6396 -0.5649 -0.6120 -0.4617 -0.5904 -0.3709 -0.5726 -0.2909 -0.5573 -0.2201 -0.5441 -0.1572 -0.5326 -0.1014 -0.5226 -0.0515 -0.5138 -0.0069 -0.5060 0.0330 -0.4993 0.0690 -0.4934 0.1015 -0.4882 0.1309 -0.4838 0.1578 -0.4799 0.1825 -0.4767 0.2053 -0.4739 0.2266 -0.4716 0.2466 -0.4697 0.2656 -0.4681 0.2840 -0.4669 0.3020 -0.4659 0.3199 -0.4651 0.3381 -0.4646 0.3569 -0.4642 0.3769 -0.4639 0.3985 -0.4637 0.4237 -0.4636 0.4539 -0.4635 0.4874 -0.4635 0.6090 -0.4635 -0.6430 -0.4634 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -22.000 0.311 -0.601 0.033 1.000 0.444 0.0000 -1.0595 Cpi Cpv ----------------- -0.6526 -0.4739 -0.5007 -0.4739 0.4676 -0.4738 0.4471 -0.4735 0.4241 -0.4729 0.4059 -0.4720 0.3891 -0.4705 0.3740 -0.4683 0.3604 -0.4651 0.3479 -0.4609 0.3366 -0.4557 0.3260 -0.4494 0.3162 -0.4423 0.3071 -0.4343 0.2985 -0.4257 0.2904 -0.4167 0.2829 -0.4075 0.2759 -0.3982 0.2696 -0.3888 0.2640 -0.3796 0.2593 -0.3703 0.2557 -0.3610 0.2534 -0.3516 0.2527 -0.3418 0.2538 -0.3313 0.2572 -0.3198 0.2633 -0.3070 0.2724 -0.2924 0.2849 -0.2755 0.3015 -0.2558 0.3225 -0.2326 0.3483 -0.2055 0.3794 -0.1739 0.4162 -0.1371 0.4588 -0.0946 0.5075 -0.0460 0.5622 0.0091 0.6226 0.0713 0.6878 0.1407 0.7566 0.2174 0.8268 0.3016 0.8945 0.3930 0.9535 0.4908 0.9930 0.5953 0.9938 0.7014 0.9203 0.8108 0.7017 0.9079 0.1868 0.9837 -0.9775 0.9900 -3.6937 0.8292 -10.4694 0.2256 -25.4873 -0.9779 -31.0786 -1.0595 -20.5764 -0.8879 -13.2308 -0.8337 -9.1336 -0.8132 -6.6946 -0.8006 -5.1310 -0.7909 -4.0602 -0.7829 -3.2868 -0.7761 -2.7040 -0.7704 -2.2500 -0.7655 -1.8866 -0.7612 -1.5895 -0.7575 -1.3423 -0.7543 -1.1338 -0.7515 -0.9559 -0.7489 -0.8029 -0.7430 -0.6702 -0.6777 -0.5545 -0.6437 -0.4531 -0.6178 -0.3639 -0.5967 -0.2852 -0.5789 -0.2156 -0.5638 -0.1537 -0.5507 -0.0987 -0.5393 -0.0496 -0.5294 -0.0057 -0.5207 0.0337 -0.5131 0.0691 -0.5066 0.1011 -0.5008 0.1302 -0.4959 0.1567 -0.4918 0.1810 -0.4882 0.2035 -0.4852 0.2245 -0.4827 0.2443 -0.4807 0.2631 -0.4790 0.2813 -0.4776 0.2992 -0.4766 0.3169 -0.4757 0.3350 -0.4751 0.3537 -0.4747 0.3737 -0.4744 0.3953 -0.4741 0.4205 -0.4740 0.4509 -0.4739 0.4845 -0.4739 0.6068 -0.4739 -0.6526 -0.4739 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -21.500 0.291 -0.572 0.029 1.000 0.463 0.0000 -1.0373 Cpi Cpv ----------------- -0.6619 -0.4685 -0.5092 -0.4685 0.4646 -0.4684 0.4439 -0.4681 0.4207 -0.4676 0.4023 -0.4667 0.3853 -0.4654 0.3699 -0.4633 0.3561 -0.4604 0.3434 -0.4566 0.3318 -0.4517 0.3209 -0.4460 0.3108 -0.4394 0.3013 -0.4321 0.2924 -0.4242 0.2839 -0.4159 0.2759 -0.4075 0.2685 -0.3990 0.2616 -0.3905 0.2555 -0.3820 0.2502 -0.3737 0.2459 -0.3653 0.2429 -0.3568 0.2415 -0.3479 0.2419 -0.3384 0.2445 -0.3280 0.2497 -0.3163 0.2579 -0.3028 0.2696 -0.2870 0.2852 -0.2685 0.3053 -0.2465 0.3303 -0.2206 0.3606 -0.1902 0.3966 -0.1547 0.4386 -0.1135 0.4868 -0.0660 0.5412 -0.0120 0.6015 0.0491 0.6671 0.1176 0.7368 0.1936 0.8086 0.2772 0.8789 0.3683 0.9419 0.4664 0.9875 0.5715 0.9978 0.6790 0.9388 0.7912 0.7437 0.8926 0.2686 0.9762 -0.8234 0.9952 -3.3963 0.8561 -9.8604 0.2886 -24.2923 -0.9025 -29.8291 -1.0373 -19.8394 -0.8575 -12.7976 -0.7983 -8.8568 -0.7765 -6.5050 -0.7635 -4.9942 -0.7536 -3.9577 -0.7455 -3.2077 -0.7388 -2.6418 -0.7331 -2.2003 -0.7282 -1.8463 -0.7240 -1.5566 -0.7203 -1.3152 -0.7171 -1.1114 -0.7143 -0.9374 -0.7118 -0.7874 -0.7095 -0.6574 -0.6727 -0.5439 -0.6351 -0.4443 -0.6091 -0.3567 -0.5885 -0.2794 -0.5713 -0.2109 -0.5565 -0.1500 -0.5438 -0.0959 -0.5327 -0.0476 -0.5230 -0.0043 -0.5146 0.0344 -0.5072 0.0694 -0.5008 0.1009 -0.4952 0.1295 -0.4904 0.1556 -0.4863 0.1797 -0.4828 0.2018 -0.4798 0.2226 -0.4773 0.2421 -0.4752 0.2607 -0.4736 0.2788 -0.4722 0.2964 -0.4711 0.3140 -0.4703 0.3320 -0.4697 0.3507 -0.4693 0.3706 -0.4690 0.3922 -0.4688 0.4175 -0.4686 0.4479 -0.4686 0.4817 -0.4685 0.6045 -0.4685 -0.6619 -0.4685 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -21.000 0.288 -0.575 0.029 1.000 0.484 0.0000 -1.0685 Cpi Cpv ----------------- -0.6711 -0.4703 -0.5175 -0.4703 0.4616 -0.4702 0.4407 -0.4699 0.4174 -0.4694 0.3987 -0.4686 0.3816 -0.4673 0.3660 -0.4653 0.3520 -0.4625 0.3390 -0.4587 0.3271 -0.4540 0.3159 -0.4484 0.3055 -0.4420 0.2956 -0.4349 0.2863 -0.4272 0.2774 -0.4192 0.2690 -0.4111 0.2611 -0.4028 0.2537 -0.3947 0.2470 -0.3866 0.2411 -0.3786 0.2362 -0.3707 0.2325 -0.3626 0.2303 -0.3542 0.2299 -0.3453 0.2317 -0.3354 0.2360 -0.3243 0.2434 -0.3115 0.2542 -0.2964 0.2689 -0.2786 0.2881 -0.2575 0.3121 -0.2324 0.3416 -0.2028 0.3768 -0.1681 0.4181 -0.1277 0.4657 -0.0811 0.5197 -0.0277 0.5799 0.0327 0.6458 0.1006 0.7163 0.1762 0.7895 0.2596 0.8622 0.3507 0.9290 0.4490 0.9805 0.5549 0.9997 0.6636 0.9549 0.7779 0.7825 0.8824 0.3462 0.9710 -0.6752 0.9973 -3.1080 0.8691 -9.2664 0.3153 -23.1211 -0.8900 -28.5998 -1.0685 -19.1121 -0.8782 -12.3690 -0.8138 -8.5823 -0.7904 -6.3166 -0.7767 -4.8581 -0.7664 -3.8554 -0.7581 -3.1288 -0.7512 -2.5796 -0.7453 -2.1504 -0.7403 -1.8059 -0.7360 -1.5235 -0.7322 -1.2880 -0.7289 -1.0888 -0.7260 -0.9186 -0.7234 -0.7718 -0.7211 -0.6444 -0.7107 -0.5331 -0.6555 -0.4354 -0.6247 -0.3494 -0.6010 -0.2733 -0.5817 -0.2060 -0.5653 -0.1462 -0.5513 -0.0929 -0.5393 -0.0453 -0.5288 -0.0028 -0.5196 0.0354 -0.5117 0.0698 -0.5048 0.1008 -0.4988 0.1290 -0.4936 0.1548 -0.4892 0.1784 -0.4854 0.2003 -0.4823 0.2207 -0.4796 0.2400 -0.4774 0.2584 -0.4756 0.2763 -0.4742 0.2938 -0.4731 0.3112 -0.4722 0.3291 -0.4716 0.3477 -0.4711 0.3676 -0.4708 0.3892 -0.4706 0.4145 -0.4704 0.4450 -0.4703 0.4789 -0.4703 0.6024 -0.4703 -0.6711 -0.4703 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -20.500 0.277 -0.562 0.027 1.000 0.498 0.0000 -1.0795 Cpi Cpv ----------------- -0.6800 -0.4669 -0.5256 -0.4669 0.4587 -0.4668 0.4377 -0.4666 0.4141 -0.4662 0.3953 -0.4654 0.3779 -0.4641 0.3621 -0.4623 0.3479 -0.4596 0.3347 -0.4561 0.3225 -0.4517 0.3110 -0.4464 0.3002 -0.4404 0.2900 -0.4337 0.2803 -0.4265 0.2710 -0.4190 0.2621 -0.4114 0.2537 -0.4037 0.2458 -0.3961 0.2385 -0.3887 0.2320 -0.3814 0.2265 -0.3741 0.2221 -0.3667 0.2192 -0.3591 0.2180 -0.3509 0.2190 -0.3419 0.2224 -0.3317 0.2289 -0.3198 0.2387 -0.3057 0.2525 -0.2889 0.2707 -0.2687 0.2939 -0.2447 0.3224 -0.2162 0.3567 -0.1825 0.3972 -0.1432 0.4442 -0.0976 0.4978 -0.0453 0.5578 0.0142 0.6239 0.0813 0.6950 0.1563 0.7695 0.2392 0.8445 0.3300 0.9149 0.4285 0.9719 0.5349 0.9998 0.6448 0.9685 0.7613 0.8182 0.8691 0.4195 0.9636 -0.5331 0.9992 -2.8288 0.8860 -8.6876 0.3560 -21.9740 -0.8508 -27.3912 -1.0795 -18.3947 -0.8788 -11.9452 -0.8085 -8.3103 -0.7834 -6.1295 -0.7690 -4.7226 -0.7584 -3.7535 -0.7500 -3.0500 -0.7429 -2.5173 -0.7370 -2.1005 -0.7319 -1.7654 -0.7275 -1.4902 -0.7237 -1.2605 -0.7203 -1.0661 -0.7174 -0.8996 -0.7148 -0.7560 -0.7124 -0.6312 -0.7102 -0.5221 -0.6613 -0.4262 -0.6267 -0.3418 -0.6016 -0.2671 -0.5814 -0.2010 -0.5645 -0.1421 -0.5500 -0.0897 -0.5376 -0.0430 -0.5268 -0.0011 -0.5175 0.0365 -0.5093 0.0703 -0.5023 0.1009 -0.4961 0.1287 -0.4909 0.1540 -0.4863 0.1773 -0.4825 0.1989 -0.4792 0.2190 -0.4765 0.2381 -0.4743 0.2562 -0.4724 0.2739 -0.4710 0.2912 -0.4698 0.3086 -0.4689 0.3263 -0.4683 0.3448 -0.4678 0.3647 -0.4674 0.3863 -0.4672 0.4116 -0.4671 0.4421 -0.4670 0.4762 -0.4670 0.6003 -0.4670 -0.6800 -0.4669 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -20.000 0.268 -0.550 0.025 1.000 0.524 0.0000 -1.0885 Cpi Cpv ----------------- -0.6886 -0.4647 -0.5336 -0.4647 0.4559 -0.4645 0.4347 -0.4643 0.4109 -0.4639 0.3920 -0.4632 0.3744 -0.4620 0.3584 -0.4602 0.3439 -0.4577 0.3304 -0.4544 0.3179 -0.4503 0.3062 -0.4453 0.2951 -0.4396 0.2845 -0.4333 0.2744 -0.4265 0.2647 -0.4195 0.2554 -0.4123 0.2465 -0.4052 0.2380 -0.3982 0.2302 -0.3913 0.2231 -0.3846 0.2168 -0.3779 0.2117 -0.3712 0.2081 -0.3643 0.2061 -0.3569 0.2062 -0.3487 0.2088 -0.3393 0.2143 -0.3283 0.2233 -0.3151 0.2361 -0.2993 0.2533 -0.2802 0.2754 -0.2572 0.3030 -0.2298 0.3364 -0.1972 0.3762 -0.1589 0.4225 -0.1144 0.4755 -0.0631 0.5353 -0.0045 0.6013 0.0618 0.6730 0.1360 0.7486 0.2183 0.8257 0.3089 0.8994 0.4075 0.9618 0.5142 0.9979 0.6253 0.9797 0.7438 0.8508 0.8549 0.4885 0.9553 -0.3971 1.0000 -2.5590 0.9016 -8.1241 0.3981 -20.8515 -0.8109 -26.2034 -1.0885 -17.6874 -0.8773 -11.5263 -0.8005 -8.0408 -0.7735 -5.9438 -0.7585 -4.5878 -0.7477 -3.6520 -0.7390 -2.9713 -0.7319 -2.4551 -0.7258 -2.0505 -0.7207 -1.7247 -0.7162 -1.4568 -0.7124 -1.2329 -0.7090 -1.0431 -0.7060 -0.8805 -0.7034 -0.7400 -0.7010 -0.6178 -0.6988 -0.5109 -0.6844 -0.4169 -0.6363 -0.3341 -0.6074 -0.2607 -0.5853 -0.1957 -0.5671 -0.1379 -0.5517 -0.0864 -0.5385 -0.0404 -0.5271 0.0008 -0.5173 0.0377 -0.5088 0.0710 -0.5014 0.1011 -0.4950 0.1284 -0.4895 0.1534 -0.4848 0.1763 -0.4808 0.1976 -0.4774 0.2175 -0.4746 0.2362 -0.4723 0.2542 -0.4704 0.2716 -0.4688 0.2888 -0.4676 0.3060 -0.4667 0.3236 -0.4660 0.3421 -0.4655 0.3618 -0.4652 0.3834 -0.4649 0.4088 -0.4648 0.4394 -0.4647 0.4735 -0.4647 0.5983 -0.4647 -0.6886 -0.4647 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -19.500 0.260 -0.542 0.024 1.000 0.540 0.0000 -1.1080 Cpi Cpv ----------------- -0.6971 -0.4601 -0.5412 -0.4601 0.4531 -0.4600 0.4318 -0.4598 0.4079 -0.4594 0.3887 -0.4587 0.3709 -0.4576 0.3547 -0.4559 0.3400 -0.4536 0.3262 -0.4504 0.3135 -0.4465 0.3015 -0.4419 0.2900 -0.4365 0.2791 -0.4306 0.2686 -0.4243 0.2585 -0.4177 0.2487 -0.4110 0.2393 -0.4044 0.2303 -0.3979 0.2219 -0.3916 0.2141 -0.3855 0.2073 -0.3795 0.2014 -0.3735 0.1970 -0.3673 0.1942 -0.3607 0.1935 -0.3533 0.1952 -0.3448 0.1998 -0.3346 0.2077 -0.3224 0.2196 -0.3076 0.2358 -0.2895 0.2569 -0.2676 0.2835 -0.2413 0.3160 -0.2098 0.3548 -0.1726 0.4004 -0.1292 0.4528 -0.0789 0.5122 -0.0213 0.5782 0.0441 0.6503 0.1176 0.7269 0.1993 0.8058 0.2896 0.8827 0.3882 0.9501 0.4946 0.9941 0.6087 0.9885 0.7258 0.8801 0.8439 0.5533 0.9446 -0.2671 0.9998 -2.2984 0.9104 -7.5762 0.4399 -19.7538 -0.7837 -25.0370 -1.1080 -16.9905 -0.8856 -11.1124 -0.8014 -7.7739 -0.7724 -5.7595 -0.7566 -4.4538 -0.7454 -3.5509 -0.7366 -2.8928 -0.7293 -2.3929 -0.7232 -2.0004 -0.7179 -1.6839 -0.7134 -1.4233 -0.7095 -1.2051 -0.7060 -1.0200 -0.7030 -0.8612 -0.7003 -0.7238 -0.6979 -0.6042 -0.6957 -0.4995 -0.6937 -0.4074 -0.6454 -0.3261 -0.6119 -0.2542 -0.5875 -0.1904 -0.5679 -0.1336 -0.5514 -0.0830 -0.5374 -0.0377 -0.5254 0.0027 -0.5151 0.0391 -0.5061 0.0718 -0.4984 0.1014 -0.4917 0.1283 -0.4859 0.1529 -0.4810 0.1755 -0.4768 0.1964 -0.4733 0.2160 -0.4704 0.2345 -0.4680 0.2522 -0.4660 0.2695 -0.4644 0.2865 -0.4632 0.3035 -0.4622 0.3210 -0.4615 0.3394 -0.4610 0.3591 -0.4606 0.3806 -0.4604 0.4060 -0.4602 0.4367 -0.4601 0.4710 -0.4601 0.5963 -0.4601 -0.6971 -0.4601 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -19.000 0.252 -0.530 0.023 1.000 0.569 0.0000 -1.1206 Cpi Cpv ----------------- -0.7053 -0.4563 -0.5487 -0.4563 0.4504 -0.4562 0.4290 -0.4560 0.4048 -0.4556 0.3855 -0.4550 0.3675 -0.4540 0.3511 -0.4524 0.3361 -0.4502 0.3222 -0.4473 0.3092 -0.4436 0.2968 -0.4392 0.2851 -0.4342 0.2738 -0.4286 0.2629 -0.4227 0.2523 -0.4166 0.2421 -0.4104 0.2322 -0.4043 0.2227 -0.3984 0.2137 -0.3926 0.2053 -0.3871 0.1977 -0.3818 0.1912 -0.3764 0.1860 -0.3710 0.1824 -0.3651 0.1808 -0.3585 0.1816 -0.3509 0.1852 -0.3417 0.1922 -0.3304 0.2030 -0.3166 0.2181 -0.2996 0.2382 -0.2788 0.2638 -0.2536 0.2953 -0.2233 0.3332 -0.1873 0.3779 -0.1449 0.4297 -0.0957 0.4886 -0.0392 0.5545 0.0252 0.6268 0.0979 0.7044 0.1790 0.7850 0.2688 0.8648 0.3673 0.9368 0.4738 0.9883 0.5891 0.9948 0.7073 0.9063 0.8291 0.6137 0.9342 -0.1433 0.9986 -2.0473 0.9247 -7.0440 0.4777 -18.6814 -0.7398 -23.8923 -1.1206 -16.3042 -0.8865 -10.7037 -0.7945 -7.5097 -0.7633 -5.5766 -0.7468 -4.3207 -0.7353 -3.4502 -0.7263 -2.8146 -0.7189 -2.3308 -0.7127 -1.9503 -0.7074 -1.6430 -0.7028 -1.3896 -0.6988 -1.1772 -0.6953 -0.9966 -0.6923 -0.8416 -0.6895 -0.7074 -0.6871 -0.5905 -0.6849 -0.4879 -0.6828 -0.3977 -0.6728 -0.3180 -0.6228 -0.2474 -0.5939 -0.1848 -0.5718 -0.1290 -0.5537 -0.0793 -0.5385 -0.0349 -0.5256 0.0049 -0.5145 0.0406 -0.5049 0.0728 -0.4967 0.1019 -0.4896 0.1284 -0.4835 0.1525 -0.4783 0.1747 -0.4739 0.1953 -0.4702 0.2146 -0.4671 0.2329 -0.4646 0.2504 -0.4625 0.2674 -0.4608 0.2842 -0.4595 0.3011 -0.4585 0.3185 -0.4578 0.3368 -0.4572 0.3564 -0.4568 0.3780 -0.4566 0.4034 -0.4564 0.4341 -0.4563 0.4685 -0.4563 0.5944 -0.4563 -0.7053 -0.4563 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -18.500 0.239 -0.508 0.020 1.000 0.592 0.0000 -1.1250 Cpi Cpv ----------------- -0.7132 -0.4516 -0.5560 -0.4516 0.4478 -0.4515 0.4262 -0.4514 0.4019 -0.4510 0.3824 -0.4505 0.3642 -0.4495 0.3476 -0.4481 0.3324 -0.4460 0.3182 -0.4433 0.3049 -0.4400 0.2923 -0.4359 0.2802 -0.4313 0.2685 -0.4262 0.2573 -0.4208 0.2463 -0.4153 0.2356 -0.4097 0.2252 -0.4042 0.2151 -0.3990 0.2055 -0.3939 0.1965 -0.3891 0.1883 -0.3845 0.1810 -0.3800 0.1750 -0.3753 0.1706 -0.3703 0.1681 -0.3647 0.1680 -0.3580 0.1706 -0.3498 0.1766 -0.3397 0.1863 -0.3270 0.2005 -0.3111 0.2195 -0.2915 0.2439 -0.2675 0.2744 -0.2385 0.3114 -0.2037 0.3552 -0.1626 0.4062 -0.1146 0.4646 -0.0592 0.5303 0.0042 0.6027 0.0758 0.6810 0.1562 0.7631 0.2454 0.8455 0.3437 0.9220 0.4503 0.9806 0.5665 0.9986 0.6861 0.9292 0.8116 0.6698 0.9217 -0.0258 0.9961 -1.8056 0.9397 -6.5276 0.5210 -17.6345 -0.6824 -22.7696 -1.1250 -15.6286 -0.8788 -10.3002 -0.7777 -7.2482 -0.7441 -5.3953 -0.7268 -4.1883 -0.7150 -3.3499 -0.7059 -2.7365 -0.6984 -2.2687 -0.6921 -1.9002 -0.6868 -1.6020 -0.6822 -1.3558 -0.6782 -1.1490 -0.6747 -0.9732 -0.6716 -0.8219 -0.6689 -0.6909 -0.6664 -0.5765 -0.6642 -0.4762 -0.6622 -0.3878 -0.6603 -0.3098 -0.6299 -0.2405 -0.5950 -0.1791 -0.5708 -0.1243 -0.5517 -0.0755 -0.5360 -0.0319 -0.5226 0.0072 -0.5111 0.0423 -0.5013 0.0739 -0.4928 0.1025 -0.4856 0.1285 -0.4794 0.1523 -0.4741 0.1741 -0.4696 0.1944 -0.4658 0.2134 -0.4627 0.2314 -0.4601 0.2486 -0.4580 0.2655 -0.4563 0.2821 -0.4549 0.2989 -0.4539 0.3161 -0.4531 0.3343 -0.4526 0.3539 -0.4522 0.3754 -0.4519 0.4008 -0.4518 0.4316 -0.4517 0.4661 -0.4516 0.5925 -0.4516 -0.7132 -0.4516 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -18.000 0.240 -0.513 0.021 1.000 0.616 0.0000 -1.1617 Cpi Cpv ----------------- -0.7209 -0.4439 -0.5630 -0.4439 0.4453 -0.4438 0.4235 -0.4437 0.3991 -0.4434 0.3794 -0.4428 0.3610 -0.4419 0.3442 -0.4406 0.3288 -0.4386 0.3143 -0.4360 0.3007 -0.4328 0.2878 -0.4290 0.2754 -0.4246 0.2634 -0.4197 0.2517 -0.4146 0.2403 -0.4094 0.2291 -0.4041 0.2183 -0.3990 0.2077 -0.3942 0.1975 -0.3896 0.1878 -0.3853 0.1789 -0.3812 0.1709 -0.3772 0.1641 -0.3732 0.1589 -0.3689 0.1555 -0.3640 0.1544 -0.3581 0.1561 -0.3508 0.1610 -0.3415 0.1697 -0.3298 0.1827 -0.3150 0.2006 -0.2965 0.2240 -0.2736 0.2533 -0.2456 0.2893 -0.2120 0.3321 -0.1721 0.3824 -0.1252 0.4401 -0.0708 0.5054 -0.0085 0.5779 0.0623 0.6567 0.1419 0.7402 0.2306 0.8251 0.3285 0.9057 0.4352 0.9710 0.5519 1.0000 0.6724 0.9489 0.8002 0.7216 0.9136 0.0856 0.9941 -1.5736 0.9473 -6.0273 0.5412 -16.6134 -0.6680 -21.6693 -1.1617 -14.9639 -0.9031 -9.9021 -0.7934 -6.9896 -0.7572 -5.2155 -0.7390 -4.0569 -0.7267 -3.2501 -0.7173 -2.6587 -0.7097 -2.2067 -0.7033 -1.8500 -0.6978 -1.5610 -0.6931 -1.3219 -0.6890 -1.1208 -0.6854 -0.9495 -0.6822 -0.8021 -0.6794 -0.6741 -0.6768 -0.5624 -0.6745 -0.4643 -0.6725 -0.3778 -0.6706 -0.3013 -0.6688 -0.2335 -0.6124 -0.1732 -0.5815 -0.1195 -0.5584 -0.0716 -0.5396 -0.0288 -0.5240 0.0096 -0.5108 0.0441 -0.4996 0.0752 -0.4900 0.1033 -0.4818 0.1288 -0.4748 0.1521 -0.4689 0.1736 -0.4639 0.1936 -0.4597 0.2123 -0.4562 0.2300 -0.4533 0.2470 -0.4509 0.2636 -0.4490 0.2801 -0.4476 0.2967 -0.4464 0.3138 -0.4456 0.3319 -0.4450 0.3514 -0.4445 0.3729 -0.4443 0.3983 -0.4441 0.4292 -0.4440 0.4637 -0.4439 0.5907 -0.4439 -0.7209 -0.4439 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -17.500 0.226 -0.488 0.018 1.000 0.651 0.0000 -1.1630 Cpi Cpv ----------------- -0.7284 -0.4402 -0.5698 -0.4402 0.4429 -0.4401 0.4210 -0.4400 0.3963 -0.4397 0.3765 -0.4392 0.3579 -0.4384 0.3409 -0.4371 0.3252 -0.4354 0.3105 -0.4330 0.2967 -0.4300 0.2834 -0.4265 0.2707 -0.4225 0.2583 -0.4181 0.2463 -0.4135 0.2344 -0.4088 0.2228 -0.4042 0.2114 -0.3997 0.2003 -0.3954 0.1895 -0.3915 0.1792 -0.3879 0.1696 -0.3845 0.1609 -0.3813 0.1533 -0.3781 0.1472 -0.3747 0.1429 -0.3707 0.1408 -0.3657 0.1415 -0.3594 0.1454 -0.3513 0.1530 -0.3407 0.1648 -0.3271 0.1816 -0.3098 0.2038 -0.2882 0.2321 -0.2615 0.2669 -0.2292 0.3088 -0.1906 0.3581 -0.1450 0.4152 -0.0918 0.4800 -0.0307 0.5524 0.0391 0.6316 0.1177 0.7162 0.2057 0.8034 0.3032 0.8878 0.4100 0.9595 0.5273 0.9989 0.6491 0.9655 0.7802 0.7690 0.8986 0.1907 0.9893 -1.3511 0.9605 -5.5431 0.5850 -15.6185 -0.6035 -20.5917 -1.1630 -14.3105 -0.8929 -9.5095 -0.7719 -6.7339 -0.7326 -5.0374 -0.7134 -3.9264 -0.7009 -3.1509 -0.6914 -2.5811 -0.6837 -2.1449 -0.6773 -1.7999 -0.6718 -1.5198 -0.6671 -1.2878 -0.6630 -1.0924 -0.6594 -0.9257 -0.6562 -0.7821 -0.6534 -0.6572 -0.6508 -0.5481 -0.6485 -0.4522 -0.6464 -0.3676 -0.6446 -0.2927 -0.6428 -0.2262 -0.6368 -0.1671 -0.5889 -0.1145 -0.5615 -0.0675 -0.5408 -0.0255 -0.5240 0.0122 -0.5099 0.0460 -0.4980 0.0766 -0.4880 0.1041 -0.4794 0.1292 -0.4722 0.1522 -0.4660 0.1733 -0.4608 0.1929 -0.4564 0.2113 -0.4528 0.2287 -0.4498 0.2455 -0.4474 0.2619 -0.4455 0.2782 -0.4440 0.2946 -0.4428 0.3117 -0.4419 0.3296 -0.4413 0.3491 -0.4408 0.3705 -0.4406 0.3959 -0.4404 0.4268 -0.4403 0.4615 -0.4402 0.5889 -0.4402 -0.7284 -0.4402 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -17.000 0.214 -0.464 0.016 1.000 0.687 0.0000 -1.1684 Cpi Cpv ----------------- -0.7356 -0.4358 -0.5764 -0.4358 0.4405 -0.4357 0.4185 -0.4356 0.3937 -0.4353 0.3736 -0.4349 0.3549 -0.4341 0.3376 -0.4330 0.3218 -0.4313 0.3068 -0.4292 0.2927 -0.4265 0.2792 -0.4233 0.2661 -0.4197 0.2534 -0.4157 0.2410 -0.4115 0.2287 -0.4073 0.2166 -0.4032 0.2047 -0.3993 0.1930 -0.3956 0.1816 -0.3923 0.1707 -0.3894 0.1604 -0.3867 0.1509 -0.3843 0.1425 -0.3819 0.1355 -0.3793 0.1303 -0.3762 0.1273 -0.3722 0.1269 -0.3669 0.1297 -0.3598 0.1362 -0.3504 0.1469 -0.3380 0.1625 -0.3219 0.1836 -0.3016 0.2106 -0.2762 0.2443 -0.2453 0.2851 -0.2079 0.3335 -0.1636 0.3898 -0.1118 0.4540 -0.0518 0.5262 0.0168 0.6057 0.0945 0.6913 0.1817 0.7804 0.2787 0.8684 0.3854 0.9460 0.5032 0.9954 0.6262 0.9788 0.7602 0.8120 0.8832 0.2895 0.9834 -1.1384 0.9714 -5.0752 0.6243 -14.6501 -0.5442 -19.5371 -1.1684 -13.6684 -0.8883 -9.1225 -0.7553 -6.4812 -0.7124 -4.8610 -0.6920 -3.7968 -0.6791 -3.0522 -0.6695 -2.5038 -0.6617 -2.0831 -0.6553 -1.7498 -0.6498 -1.4787 -0.6451 -1.2537 -0.6409 -1.0639 -0.6373 -0.9018 -0.6341 -0.7619 -0.6313 -0.6402 -0.6287 -0.5336 -0.6264 -0.4399 -0.6243 -0.3572 -0.6225 -0.2839 -0.6207 -0.2188 -0.6191 -0.1609 -0.6101 -0.1093 -0.5689 -0.0632 -0.5440 -0.0220 -0.5250 0.0149 -0.5097 0.0481 -0.4969 0.0781 -0.4861 0.1052 -0.4770 0.1298 -0.4693 0.1523 -0.4628 0.1731 -0.4573 0.1923 -0.4528 0.2104 -0.4490 0.2276 -0.4458 0.2441 -0.4433 0.2603 -0.4413 0.2764 -0.4397 0.2927 -0.4385 0.3096 -0.4376 0.3274 -0.4369 0.3468 -0.4364 0.3682 -0.4361 0.3936 -0.4360 0.4246 -0.4358 0.4593 -0.4358 0.5872 -0.4358 -0.7356 -0.4358 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -16.500 0.205 -0.446 0.014 1.000 0.723 0.0000 -1.1774 Cpi Cpv ----------------- -0.7426 -0.4309 -0.5828 -0.4309 0.4382 -0.4308 0.4160 -0.4307 0.3911 -0.4305 0.3709 -0.4301 0.3520 -0.4294 0.3345 -0.4283 0.3184 -0.4268 0.3032 -0.4248 0.2888 -0.4223 0.2750 -0.4194 0.2616 -0.4161 0.2485 -0.4125 0.2357 -0.4087 0.2230 -0.4049 0.2104 -0.4013 0.1980 -0.3978 0.1858 -0.3947 0.1738 -0.3920 0.1622 -0.3897 0.1512 -0.3877 0.1410 -0.3859 0.1318 -0.3842 0.1239 -0.3824 0.1178 -0.3802 0.1138 -0.3771 0.1124 -0.3728 0.1141 -0.3668 0.1194 -0.3584 0.1290 -0.3472 0.1434 -0.3324 0.1632 -0.3133 0.1890 -0.2893 0.2215 -0.2596 0.2612 -0.2236 0.3085 -0.1806 0.3639 -0.1301 0.4275 -0.0713 0.4994 -0.0039 0.5790 0.0728 0.6653 0.1592 0.7562 0.2556 0.8474 0.3621 0.9307 0.4802 0.9894 0.6042 0.9889 0.7408 0.8506 0.8680 0.3819 0.9767 -0.9355 0.9798 -4.6238 0.6587 -13.7084 -0.4914 -18.5059 -1.1774 -13.0379 -0.8905 -8.7413 -0.7449 -6.2316 -0.6979 -4.6863 -0.6762 -3.6682 -0.6628 -2.9541 -0.6530 -2.4269 -0.6452 -2.0215 -0.6387 -1.6997 -0.6332 -1.4375 -0.6284 -1.2195 -0.6242 -1.0353 -0.6206 -0.8777 -0.6174 -0.7415 -0.6145 -0.6229 -0.6119 -0.5190 -0.6096 -0.4275 -0.6075 -0.3466 -0.6056 -0.2749 -0.6039 -0.2112 -0.6023 -0.1546 -0.6008 -0.1040 -0.5937 -0.0588 -0.5542 -0.0184 -0.5304 0.0178 -0.5123 0.0504 -0.4977 0.0798 -0.4857 0.1063 -0.4757 0.1305 -0.4672 0.1526 -0.4601 0.1730 -0.4541 0.1919 -0.4492 0.2097 -0.4451 0.2265 -0.4417 0.2428 -0.4390 0.2588 -0.4368 0.2747 -0.4351 0.2908 -0.4338 0.3076 -0.4328 0.3253 -0.4321 0.3446 -0.4316 0.3660 -0.4313 0.3914 -0.4311 0.4224 -0.4310 0.4572 -0.4309 0.5856 -0.4309 -0.7426 -0.4309 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -16.000 0.196 -0.425 0.012 1.000 0.764 0.0000 -1.1816 Cpi Cpv ----------------- -0.7493 -0.4267 -0.5889 -0.4267 0.4360 -0.4266 0.4137 -0.4265 0.3886 -0.4263 0.3682 -0.4260 0.3491 -0.4253 0.3315 -0.4244 0.3151 -0.4230 0.2997 -0.4211 0.2851 -0.4189 0.2709 -0.4162 0.2572 -0.4131 0.2438 -0.4098 0.2306 -0.4064 0.2174 -0.4031 0.2044 -0.3998 0.1915 -0.3969 0.1787 -0.3943 0.1661 -0.3921 0.1539 -0.3903 0.1421 -0.3889 0.1311 -0.3878 0.1211 -0.3869 0.1124 -0.3859 0.1053 -0.3844 0.1003 -0.3823 0.0979 -0.3790 0.0984 -0.3740 0.1026 -0.3668 0.1110 -0.3567 0.1241 -0.3431 0.1427 -0.3253 0.1673 -0.3026 0.1985 -0.2743 0.2370 -0.2397 0.2832 -0.1981 0.3376 -0.1488 0.4005 -0.0914 0.4718 -0.0251 0.5514 0.0505 0.6384 0.1360 0.7308 0.2318 0.8250 0.3379 0.9134 0.4562 0.9810 0.5812 0.9957 0.7202 0.8847 0.8515 0.4680 0.9688 -0.7424 0.9871 -4.1891 0.6928 -12.7938 -0.4352 -17.4983 -1.1816 -12.4191 -0.8929 -8.3659 -0.7344 -5.9851 -0.6826 -4.5134 -0.6593 -3.5407 -0.6453 -2.8566 -0.6353 -2.3503 -0.6273 -1.9601 -0.6208 -1.6497 -0.6152 -1.3963 -0.6104 -1.1852 -0.6062 -1.0066 -0.6025 -0.8535 -0.5993 -0.7210 -0.5964 -0.6055 -0.5938 -0.5042 -0.5915 -0.4149 -0.5893 -0.3359 -0.5874 -0.2658 -0.5857 -0.2035 -0.5841 -0.1480 -0.5826 -0.0985 -0.5813 -0.0543 -0.5800 -0.0147 -0.5436 0.0208 -0.5195 0.0528 -0.5018 0.0816 -0.4877 0.1076 -0.4762 0.1313 -0.4667 0.1530 -0.4588 0.1730 -0.4522 0.1915 -0.4467 0.2090 -0.4422 0.2256 -0.4385 0.2417 -0.4355 0.2574 -0.4331 0.2731 -0.4313 0.2891 -0.4299 0.3057 -0.4288 0.3233 -0.4280 0.3425 -0.4275 0.3638 -0.4271 0.3892 -0.4269 0.4203 -0.4268 0.4552 -0.4267 0.5840 -0.4267 -0.7493 -0.4267 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -15.500 0.180 -0.387 0.007 1.000 0.831 0.0000 -1.1632 Cpi Cpv ----------------- -0.7558 -0.4290 -0.5948 -0.4290 0.4339 -0.4289 0.4115 -0.4288 0.3862 -0.4286 0.3656 -0.4283 0.3464 -0.4277 0.3285 -0.4268 0.3120 -0.4255 0.2963 -0.4238 0.2814 -0.4217 0.2670 -0.4193 0.2529 -0.4165 0.2391 -0.4135 0.2255 -0.4105 0.2119 -0.4075 0.1984 -0.4047 0.1850 -0.4021 0.1717 -0.4000 0.1585 -0.3983 0.1456 -0.3971 0.1332 -0.3963 0.1214 -0.3959 0.1105 -0.3956 0.1009 -0.3953 0.0929 -0.3948 0.0869 -0.3935 0.0833 -0.3911 0.0828 -0.3872 0.0858 -0.3811 0.0929 -0.3722 0.1048 -0.3598 0.1220 -0.3433 0.1453 -0.3220 0.1753 -0.2951 0.2125 -0.2619 0.2576 -0.2217 0.3109 -0.1739 0.3729 -0.1178 0.4437 -0.0528 0.5231 0.0217 0.6104 0.1061 0.7042 0.2012 0.8010 0.3070 0.8942 0.4254 0.9701 0.5514 0.9994 0.6931 0.9145 0.8292 0.5478 0.9569 -0.5592 0.9941 -3.7710 0.7354 -11.9065 -0.3531 -16.5148 -1.1632 -11.8123 -0.8823 -7.9965 -0.7096 -5.7419 -0.6517 -4.3423 -0.6262 -3.4143 -0.6115 -2.7597 -0.6011 -2.2740 -0.5931 -1.8989 -0.5865 -1.5997 -0.5810 -1.3550 -0.5762 -1.1509 -0.5720 -0.9778 -0.5684 -0.8292 -0.5651 -0.7004 -0.5623 -0.5880 -0.5597 -0.4893 -0.5573 -0.4021 -0.5552 -0.3250 -0.5533 -0.2565 -0.5516 -0.1956 -0.5500 -0.1413 -0.5486 -0.0929 -0.5472 -0.0496 -0.5460 -0.0108 -0.5449 0.0240 -0.5439 0.0553 -0.5255 0.0835 -0.5033 0.1090 -0.4877 0.1323 -0.4756 0.1535 -0.4659 0.1731 -0.4581 0.1913 -0.4517 0.2085 -0.4465 0.2248 -0.4423 0.2406 -0.4389 0.2561 -0.4362 0.2716 -0.4341 0.2874 -0.4325 0.3039 -0.4313 0.3214 -0.4304 0.3406 -0.4298 0.3618 -0.4294 0.3872 -0.4292 0.4183 -0.4291 0.4532 -0.4290 0.5825 -0.4290 -0.7558 -0.4290 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -15.000 0.168 -0.349 0.001 1.000 0.911 0.0000 -1.1445 Cpi Cpv ----------------- -0.7620 -0.4369 -0.6005 -0.4369 0.4318 -0.4368 0.4093 -0.4367 0.3839 -0.4366 0.3632 -0.4362 0.3437 -0.4357 0.3257 -0.4348 0.3089 -0.4335 0.2930 -0.4318 0.2778 -0.4298 0.2631 -0.4274 0.2487 -0.4247 0.2346 -0.4217 0.2206 -0.4188 0.2066 -0.4159 0.1926 -0.4132 0.1787 -0.4109 0.1647 -0.4089 0.1509 -0.4075 0.1374 -0.4066 0.1242 -0.4061 0.1117 -0.4060 0.1000 -0.4062 0.0895 -0.4065 0.0805 -0.4065 0.0735 -0.4059 0.0689 -0.4044 0.0672 -0.4013 0.0689 -0.3961 0.0748 -0.3883 0.0854 -0.3771 0.1013 -0.3618 0.1232 -0.3417 0.1518 -0.3161 0.1878 -0.2842 0.2316 -0.2454 0.2838 -0.1990 0.3448 -0.1442 0.4149 -0.0805 0.4939 -0.0072 0.5815 0.0762 0.6763 0.1705 0.7755 0.2759 0.8731 0.3943 0.9568 0.5212 0.9998 0.6654 0.9399 0.8059 0.6211 0.9433 -0.3859 0.9983 -3.3698 0.7737 -11.0468 -0.2739 -15.5555 -1.1445 -11.2176 -0.8789 -7.6332 -0.6918 -5.5020 -0.6264 -4.1731 -0.5983 -3.2890 -0.5826 -2.6635 -0.5719 -2.1982 -0.5637 -1.8378 -0.5571 -1.5499 -0.5515 -1.3138 -0.5467 -1.1164 -0.5425 -0.9488 -0.5389 -0.8047 -0.5356 -0.6797 -0.5327 -0.5703 -0.5302 -0.4742 -0.5278 -0.3892 -0.5257 -0.3140 -0.5238 -0.2471 -0.5221 -0.1876 -0.5205 -0.1345 -0.5191 -0.0871 -0.5178 -0.0447 -0.5166 -0.0067 -0.5155 0.0273 -0.5145 0.0580 -0.5136 0.0856 -0.5128 0.1106 -0.5121 0.1334 -0.5114 0.1542 -0.4925 0.1734 -0.4787 0.1913 -0.4686 0.2081 -0.4609 0.2241 -0.4549 0.2397 -0.4501 0.2550 -0.4465 0.2703 -0.4437 0.2859 -0.4415 0.3022 -0.4399 0.3196 -0.4388 0.3387 -0.4380 0.3599 -0.4375 0.3852 -0.4372 0.4164 -0.4370 0.4513 -0.4369 0.5810 -0.4369 -0.7620 -0.4369 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -14.500 0.146 -0.275 -0.015 1.000 0.998 0.0000 -1.1086 Cpi Cpv ----------------- -0.7679 -0.4526 -0.6059 -0.4526 0.4299 -0.4525 0.4072 -0.4525 0.3816 -0.4523 0.3608 -0.4520 0.3412 -0.4514 0.3229 -0.4505 0.3059 -0.4493 0.2898 -0.4478 0.2743 -0.4458 0.2593 -0.4435 0.2446 -0.4410 0.2301 -0.4382 0.2157 -0.4355 0.2013 -0.4328 0.1869 -0.4304 0.1724 -0.4284 0.1579 -0.4268 0.1435 -0.4257 0.1293 -0.4251 0.1154 -0.4251 0.1021 -0.4256 0.0896 -0.4263 0.0782 -0.4272 0.0682 -0.4279 0.0601 -0.4282 0.0544 -0.4275 0.0515 -0.4253 0.0521 -0.4213 0.0566 -0.4146 0.0659 -0.4046 0.0804 -0.3906 0.1010 -0.3719 0.1282 -0.3478 0.1628 -0.3174 0.2052 -0.2801 0.2562 -0.2352 0.3162 -0.1820 0.3854 -0.1197 0.4640 -0.0478 0.5517 0.0344 0.6473 0.1277 0.7485 0.2328 0.8501 0.3502 0.9411 0.4811 0.9970 0.6233 0.9608 0.7758 0.6880 0.9175 -0.2227 0.9999 -2.9856 0.8100 -10.2149 -0.1359 -14.6207 -1.1086 -10.6353 -0.8616 -7.2761 -0.6560 -5.2654 -0.5790 -4.0059 -0.5468 -3.1649 -0.5296 -2.5680 -0.5183 -2.1227 -0.5100 -1.7770 -0.5033 -1.5001 -0.4978 -1.2726 -0.4930 -1.0820 -0.4889 -0.9198 -0.4853 -0.7802 -0.4822 -0.6588 -0.4793 -0.5525 -0.4768 -0.4589 -0.4745 -0.3762 -0.4724 -0.3028 -0.4706 -0.2375 -0.4689 -0.1794 -0.4673 -0.1275 -0.4659 -0.0812 -0.4646 -0.0397 -0.4635 -0.0025 -0.4624 0.0308 -0.4614 0.0608 -0.4606 0.0878 -0.4598 0.1123 -0.4591 0.1346 -0.4585 0.1550 -0.4580 0.1738 -0.4575 0.1913 -0.4571 0.2078 -0.4567 0.2236 -0.4565 0.2388 -0.4562 0.2539 -0.4560 0.2690 -0.4559 0.2844 -0.4557 0.3006 -0.4556 0.3179 -0.4556 0.3369 -0.4553 0.3580 -0.4540 0.3834 -0.4533 0.4145 -0.4529 0.4496 -0.4527 0.5797 -0.4526 -0.7679 -0.4526 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -14.000 0.139 -0.253 -0.019 1.000 1.000 0.0000 -1.0962 Cpi Cpv ----------------- -0.7736 -0.4399 -0.6111 -0.4399 0.4280 -0.4399 0.4052 -0.4398 0.3795 -0.4396 0.3585 -0.4394 0.3387 -0.4389 0.3203 -0.4382 0.3031 -0.4371 0.2867 -0.4358 0.2709 -0.4342 0.2557 -0.4322 0.2406 -0.4301 0.2258 -0.4279 0.2110 -0.4257 0.1961 -0.4237 0.1812 -0.4219 0.1662 -0.4206 0.1512 -0.4197 0.1362 -0.4194 0.1213 -0.4196 0.1067 -0.4205 0.0926 -0.4218 0.0792 -0.4235 0.0669 -0.4253 0.0559 -0.4271 0.0468 -0.4284 0.0400 -0.4289 0.0359 -0.4281 0.0352 -0.4253 0.0385 -0.4200 0.0464 -0.4114 0.0595 -0.3990 0.0786 -0.3818 0.1044 -0.3593 0.1375 -0.3305 0.1786 -0.2949 0.2283 -0.2516 0.2870 -0.1999 0.3553 -0.1392 0.4333 -0.0687 0.5208 0.0122 0.6171 0.1043 0.7200 0.2086 0.8253 0.3253 0.9229 0.4571 0.9909 0.5991 0.9772 0.7564 0.7484 0.9025 -0.0695 0.9988 -2.6185 0.8353 -9.4112 -0.0807 -13.7108 -1.0962 -10.0654 -0.8771 -6.9254 -0.6567 -5.0323 -0.5703 -3.8406 -0.5345 -3.0419 -0.5158 -2.4732 -0.5039 -2.0477 -0.4952 -1.7164 -0.4884 -1.4505 -0.4828 -1.2314 -0.4780 -1.0475 -0.4738 -0.8908 -0.4702 -0.7555 -0.4670 -0.6378 -0.4641 -0.5345 -0.4615 -0.4435 -0.4592 -0.3630 -0.4571 -0.2914 -0.4552 -0.2278 -0.4535 -0.1710 -0.4520 -0.1204 -0.4505 -0.0751 -0.4492 -0.0345 -0.4480 0.0018 -0.4470 0.0344 -0.4460 0.0637 -0.4451 0.0902 -0.4443 0.1141 -0.4436 0.1359 -0.4430 0.1559 -0.4425 0.1743 -0.4420 0.1915 -0.4416 0.2077 -0.4412 0.2231 -0.4409 0.2381 -0.4407 0.2530 -0.4405 0.2679 -0.4403 0.2831 -0.4402 0.2992 -0.4401 0.3163 -0.4400 0.3352 -0.4400 0.3563 -0.4399 0.3816 -0.4399 0.4128 -0.4399 0.4478 -0.4399 0.5783 -0.4399 -0.7736 -0.4399 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -13.500 0.132 -0.235 -0.021 1.000 1.000 0.0000 -1.0840 Cpi Cpv ----------------- -0.7791 -0.4262 -0.6161 -0.4262 0.4262 -0.4262 0.4033 -0.4261 0.3775 -0.4260 0.3563 -0.4258 0.3363 -0.4254 0.3177 -0.4248 0.3003 -0.4239 0.2836 -0.4228 0.2677 -0.4215 0.2521 -0.4199 0.2367 -0.4182 0.2215 -0.4165 0.2064 -0.4148 0.1911 -0.4134 0.1757 -0.4122 0.1602 -0.4115 0.1446 -0.4114 0.1289 -0.4118 0.1134 -0.4128 0.0981 -0.4144 0.0832 -0.4166 0.0689 -0.4192 0.0557 -0.4220 0.0438 -0.4248 0.0336 -0.4272 0.0256 -0.4289 0.0203 -0.4293 0.0183 -0.4278 0.0203 -0.4239 0.0268 -0.4168 0.0385 -0.4059 0.0561 -0.3903 0.0804 -0.3694 0.1120 -0.3423 0.1516 -0.3083 0.1999 -0.2666 0.2574 -0.2166 0.3246 -0.1574 0.4018 -0.0885 0.4890 -0.0089 0.5857 0.0820 0.6901 0.1853 0.7985 0.3014 0.9022 0.4335 0.9816 0.5758 0.9892 0.7367 0.8024 0.8875 0.0736 0.9965 -2.2686 0.8578 -8.6358 -0.0292 -12.8261 -1.0840 -9.5082 -0.8967 -6.5810 -0.6615 -4.8027 -0.5646 -3.6775 -0.5246 -2.9202 -0.5041 -2.3791 -0.4915 -1.9731 -0.4825 -1.6561 -0.4755 -1.4009 -0.4697 -1.1903 -0.4649 -1.0130 -0.4607 -0.8616 -0.4570 -0.7308 -0.4537 -0.6167 -0.4508 -0.5165 -0.4482 -0.4280 -0.4459 -0.3496 -0.4438 -0.2799 -0.4419 -0.2179 -0.4401 -0.1625 -0.4385 -0.1131 -0.4371 -0.0688 -0.4357 -0.0292 -0.4345 0.0063 -0.4334 0.0381 -0.4325 0.0668 -0.4316 0.0927 -0.4308 0.1161 -0.4300 0.1374 -0.4294 0.1569 -0.4288 0.1750 -0.4284 0.1918 -0.4279 0.2077 -0.4276 0.2228 -0.4273 0.2375 -0.4270 0.2522 -0.4268 0.2668 -0.4267 0.2819 -0.4265 0.2978 -0.4264 0.3148 -0.4264 0.3336 -0.4263 0.3546 -0.4263 0.3799 -0.4262 0.4111 -0.4262 0.4462 -0.4262 0.5771 -0.4262 -0.7791 -0.4262 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -13.000 0.126 -0.216 -0.024 1.000 1.000 0.0000 -1.0691 Cpi Cpv ----------------- -0.7842 -0.4123 -0.6208 -0.4123 0.4245 -0.4123 0.4015 -0.4122 0.3755 -0.4121 0.3542 -0.4119 0.3341 -0.4116 0.3152 -0.4111 0.2976 -0.4104 0.2807 -0.4095 0.2645 -0.4085 0.2486 -0.4072 0.2330 -0.4060 0.2174 -0.4047 0.2018 -0.4035 0.1861 -0.4027 0.1703 -0.4021 0.1542 -0.4021 0.1381 -0.4026 0.1218 -0.4037 0.1056 -0.4055 0.0895 -0.4079 0.0738 -0.4109 0.0587 -0.4144 0.0446 -0.4182 0.0316 -0.4220 0.0204 -0.4255 0.0112 -0.4283 0.0048 -0.4299 0.0015 -0.4298 0.0021 -0.4273 0.0071 -0.4217 0.0174 -0.4123 0.0335 -0.3983 0.0562 -0.3790 0.0863 -0.3535 0.1244 -0.3212 0.1712 -0.2812 0.2273 -0.2329 0.2933 -0.1753 0.3696 -0.1079 0.4563 -0.0298 0.5531 0.0598 0.6587 0.1621 0.7699 0.2774 0.8792 0.4096 0.9691 0.5522 0.9968 0.7162 0.8499 0.8718 0.2066 0.9929 -1.9360 0.8786 -7.8890 0.0216 -11.9667 -1.0691 -8.9638 -0.9184 -6.2431 -0.6687 -4.5767 -0.5601 -3.5164 -0.5152 -2.7998 -0.4926 -2.2859 -0.4790 -1.8990 -0.4695 -1.5961 -0.4623 -1.3515 -0.4565 -1.1492 -0.4515 -0.9785 -0.4473 -0.8324 -0.4436 -0.7060 -0.4403 -0.5954 -0.4373 -0.4983 -0.4347 -0.4124 -0.4323 -0.3361 -0.4302 -0.2683 -0.4282 -0.2079 -0.4265 -0.1539 -0.4248 -0.1056 -0.4234 -0.0625 -0.4220 -0.0238 -0.4208 0.0109 -0.4197 0.0420 -0.4187 0.0700 -0.4178 0.0953 -0.4169 0.1182 -0.4162 0.1390 -0.4156 0.1581 -0.4150 0.1757 -0.4145 0.1922 -0.4141 0.2077 -0.4137 0.2226 -0.4134 0.2371 -0.4131 0.2514 -0.4129 0.2659 -0.4127 0.2808 -0.4126 0.2965 -0.4125 0.3135 -0.4124 0.3321 -0.4124 0.3531 -0.4124 0.3783 -0.4123 0.4095 -0.4123 0.4447 -0.4123 0.5759 -0.4123 -0.7842 -0.4123 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -12.500 0.121 -0.198 -0.027 1.000 1.000 0.0000 -1.0512 Cpi Cpv ----------------- -0.7891 -0.3982 -0.6253 -0.3982 0.4229 -0.3982 0.3998 -0.3981 0.3736 -0.3981 0.3522 -0.3979 0.3319 -0.3977 0.3129 -0.3973 0.2951 -0.3967 0.2779 -0.3960 0.2615 -0.3952 0.2453 -0.3943 0.2293 -0.3934 0.2134 -0.3926 0.1974 -0.3919 0.1813 -0.3916 0.1649 -0.3916 0.1484 -0.3922 0.1317 -0.3933 0.1148 -0.3952 0.0979 -0.3977 0.0811 -0.4008 0.0646 -0.4047 0.0486 -0.4090 0.0335 -0.4137 0.0196 -0.4185 0.0072 -0.4231 -0.0031 -0.4271 -0.0108 -0.4300 -0.0154 -0.4312 -0.0162 -0.4301 -0.0126 -0.4260 -0.0038 -0.4181 0.0107 -0.4058 0.0318 -0.3881 0.0603 -0.3643 0.0968 -0.3337 0.1421 -0.2955 0.1967 -0.2488 0.2614 -0.1930 0.3367 -0.1272 0.4227 -0.0506 0.5193 0.0377 0.6258 0.1388 0.7394 0.2534 0.8537 0.3854 0.9534 0.5283 0.9999 0.6951 0.8909 0.8551 0.3294 0.9882 -1.6208 0.8979 -7.1711 0.0719 -11.1330 -1.0512 -8.4325 -0.9408 -5.9119 -0.6784 -4.3543 -0.5571 -3.3574 -0.5064 -2.6806 -0.4812 -2.1935 -0.4665 -1.8254 -0.4565 -1.5363 -0.4490 -1.3023 -0.4430 -1.1081 -0.4380 -0.9440 -0.4337 -0.8032 -0.4299 -0.6810 -0.4266 -0.5741 -0.4237 -0.4799 -0.4210 -0.3966 -0.4186 -0.3225 -0.4164 -0.2565 -0.4144 -0.1977 -0.4126 -0.1451 -0.4110 -0.0981 -0.4095 -0.0559 -0.4081 -0.0182 -0.4069 0.0156 -0.4057 0.0460 -0.4047 0.0734 -0.4038 0.0980 -0.4029 0.1204 -0.4022 0.1408 -0.4015 0.1594 -0.4009 0.1766 -0.4004 0.1927 -0.4000 0.2079 -0.3996 0.2225 -0.3993 0.2367 -0.3990 0.2508 -0.3988 0.2651 -0.3986 0.2798 -0.3985 0.2954 -0.3984 0.3122 -0.3983 0.3308 -0.3983 0.3516 -0.3983 0.3768 -0.3982 0.4080 -0.3982 0.4432 -0.3982 0.5747 -0.3982 -0.7891 -0.3982 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -12.000 0.115 -0.180 -0.029 1.000 1.000 0.0000 -1.0298 Cpi Cpv ----------------- -0.7938 -0.3840 -0.6295 -0.3840 0.4214 -0.3840 0.3981 -0.3839 0.3719 -0.3839 0.3503 -0.3838 0.3298 -0.3836 0.3106 -0.3833 0.2926 -0.3829 0.2753 -0.3824 0.2585 -0.3818 0.2420 -0.3812 0.2257 -0.3807 0.2095 -0.3803 0.1931 -0.3801 0.1765 -0.3802 0.1597 -0.3808 0.1427 -0.3819 0.1254 -0.3837 0.1079 -0.3862 0.0903 -0.3894 0.0728 -0.3933 0.0554 -0.3979 0.0386 -0.4031 0.0226 -0.4087 0.0076 -0.4145 -0.0058 -0.4202 -0.0173 -0.4253 -0.0263 -0.4295 -0.0322 -0.4320 -0.0344 -0.4323 -0.0323 -0.4297 -0.0251 -0.4234 -0.0122 -0.4127 0.0073 -0.3967 0.0341 -0.3747 0.0689 -0.3458 0.1126 -0.3093 0.1657 -0.2644 0.2289 -0.2103 0.3029 -0.1461 0.3881 -0.0711 0.4844 0.0158 0.5914 0.1156 0.7070 0.2293 0.8259 0.3609 0.9345 0.5040 0.9986 0.6733 0.9254 0.8376 0.4419 0.9823 -1.3232 0.9155 -6.4821 0.1218 -10.3252 -1.0298 -7.9143 -0.9625 -5.5874 -0.6906 -4.1357 -0.5562 -3.2007 -0.4986 -2.5629 -0.4703 -2.1019 -0.4542 -1.7523 -0.4435 -1.4769 -0.4357 -1.2533 -0.4295 -1.0672 -0.4244 -0.9095 -0.4200 -0.7739 -0.4162 -0.6561 -0.4129 -0.5527 -0.4099 -0.4615 -0.4072 -0.3807 -0.4047 -0.3088 -0.4025 -0.2446 -0.4005 -0.1874 -0.3987 -0.1362 -0.3970 -0.0904 -0.3955 -0.0493 -0.3941 -0.0125 -0.3928 0.0205 -0.3917 0.0502 -0.3906 0.0768 -0.3897 0.1009 -0.3888 0.1228 -0.3881 0.1426 -0.3874 0.1608 -0.3868 0.1777 -0.3863 0.1934 -0.3858 0.2083 -0.3854 0.2225 -0.3851 0.2365 -0.3848 0.2504 -0.3846 0.2644 -0.3844 0.2789 -0.3843 0.2943 -0.3842 0.3110 -0.3841 0.3295 -0.3841 0.3503 -0.3840 0.3754 -0.3840 0.4066 -0.3840 0.4418 -0.3840 0.5736 -0.3840 -0.7938 -0.3840 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -11.500 0.110 -0.163 -0.032 1.000 1.000 0.0000 -1.0048 Cpi Cpv ----------------- -0.7981 -0.3697 -0.6335 -0.3697 0.4199 -0.3697 0.3966 -0.3696 0.3702 -0.3696 0.3485 -0.3695 0.3278 -0.3694 0.3085 -0.3692 0.2902 -0.3689 0.2727 -0.3686 0.2557 -0.3683 0.2389 -0.3680 0.2223 -0.3677 0.2057 -0.3677 0.1889 -0.3680 0.1719 -0.3686 0.1546 -0.3697 0.1371 -0.3714 0.1192 -0.3737 0.1011 -0.3768 0.0828 -0.3807 0.0645 -0.3853 0.0464 -0.3907 0.0287 -0.3967 0.0117 -0.4032 -0.0043 -0.4099 -0.0189 -0.4167 -0.0315 -0.4230 -0.0417 -0.4283 -0.0490 -0.4322 -0.0527 -0.4339 -0.0520 -0.4328 -0.0464 -0.4281 -0.0351 -0.4190 -0.0173 -0.4048 0.0077 -0.3845 0.0408 -0.3574 0.0827 -0.3227 0.1342 -0.2796 0.1959 -0.2272 0.2685 -0.1648 0.3526 -0.0914 0.4484 -0.0060 0.5557 0.0925 0.6729 0.2052 0.7956 0.3363 0.9123 0.4795 0.9928 0.6509 0.9533 0.8193 0.5442 0.9751 -1.0431 0.9315 -5.8224 0.1711 -9.5436 -1.0048 -7.4094 -0.9826 -5.2697 -0.7056 -3.9209 -0.5578 -3.0462 -0.4920 -2.4465 -0.4601 -2.0111 -0.4422 -1.6798 -0.4306 -1.4178 -0.4224 -1.2044 -0.4160 -1.0263 -0.4107 -0.8750 -0.4063 -0.7446 -0.4024 -0.6310 -0.3990 -0.5312 -0.3960 -0.4430 -0.3933 -0.3646 -0.3908 -0.2949 -0.3886 -0.2326 -0.3866 -0.1769 -0.3847 -0.1271 -0.3830 -0.0825 -0.3814 -0.0425 -0.3800 -0.0066 -0.3787 0.0255 -0.3776 0.0544 -0.3765 0.0805 -0.3755 0.1040 -0.3746 0.1252 -0.3739 0.1446 -0.3732 0.1624 -0.3725 0.1788 -0.3720 0.1942 -0.3715 0.2087 -0.3712 0.2227 -0.3708 0.2363 -0.3705 0.2500 -0.3703 0.2638 -0.3701 0.2781 -0.3700 0.2934 -0.3699 0.3099 -0.3698 0.3283 -0.3698 0.3490 -0.3697 0.3741 -0.3697 0.4053 -0.3697 0.4406 -0.3697 0.5726 -0.3697 -0.7981 -0.3697 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -11.000 0.105 -0.145 -0.034 1.000 1.000 0.0000 -1.0002 Cpi Cpv ----------------- -0.8022 -0.3554 -0.6373 -0.3554 0.4185 -0.3553 0.3951 -0.3553 0.3686 -0.3553 0.3467 -0.3553 0.3260 -0.3552 0.3064 -0.3551 0.2880 -0.3549 0.2702 -0.3548 0.2529 -0.3546 0.2359 -0.3546 0.2189 -0.3547 0.2020 -0.3550 0.1848 -0.3557 0.1674 -0.3567 0.1496 -0.3583 0.1316 -0.3605 0.1131 -0.3634 0.0944 -0.3670 0.0754 -0.3715 0.0564 -0.3768 0.0375 -0.3829 0.0189 -0.3897 0.0009 -0.3970 -0.0161 -0.4048 -0.0318 -0.4125 -0.0456 -0.4199 -0.0572 -0.4265 -0.0658 -0.4318 -0.0709 -0.4349 -0.0718 -0.4353 -0.0678 -0.4322 -0.0582 -0.4248 -0.0421 -0.4123 -0.0189 -0.3937 0.0124 -0.3685 0.0525 -0.3356 0.1022 -0.2943 0.1622 -0.2437 0.2334 -0.1831 0.3162 -0.1114 0.4112 -0.0276 0.5184 0.0695 0.6368 0.1811 0.7629 0.3115 0.8870 0.4547 0.9825 0.6280 0.9748 0.8002 0.6362 0.9668 -0.7807 0.9459 -5.1922 0.2197 -8.7884 -0.9764 -6.9180 -1.0002 -4.9590 -0.7236 -3.7099 -0.5624 -2.8940 -0.4872 -2.3315 -0.4508 -1.9213 -0.4306 -1.6078 -0.4180 -1.3591 -0.4092 -1.1558 -0.4025 -0.9856 -0.3971 -0.8406 -0.3926 -0.7153 -0.3887 -0.6059 -0.3852 -0.5096 -0.3821 -0.4243 -0.3794 -0.3485 -0.3769 -0.2809 -0.3746 -0.2204 -0.3726 -0.1664 -0.3707 -0.1179 -0.3690 -0.0745 -0.3674 -0.0356 -0.3659 -0.0007 -0.3646 0.0307 -0.3634 0.0589 -0.3623 0.0842 -0.3613 0.1071 -0.3604 0.1279 -0.3596 0.1467 -0.3589 0.1641 -0.3583 0.1801 -0.3578 0.1951 -0.3573 0.2093 -0.3569 0.2230 -0.3565 0.2363 -0.3563 0.2497 -0.3560 0.2633 -0.3558 0.2775 -0.3557 0.2926 -0.3556 0.3089 -0.3555 0.3272 -0.3554 0.3478 -0.3554 0.3729 -0.3554 0.4041 -0.3554 0.4393 -0.3554 0.5717 -0.3554 -0.8022 -0.3554 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -10.500 0.101 -0.128 -0.036 1.000 1.000 0.0000 -1.0154 Cpi Cpv ----------------- -0.8061 -0.3411 -0.6408 -0.3411 0.4173 -0.3411 0.3938 -0.3411 0.3671 -0.3410 0.3451 -0.3410 0.3242 -0.3410 0.3045 -0.3410 0.2858 -0.3409 0.2678 -0.3409 0.2503 -0.3410 0.2330 -0.3412 0.2157 -0.3415 0.1984 -0.3422 0.1809 -0.3432 0.1630 -0.3446 0.1448 -0.3467 0.1262 -0.3493 0.1072 -0.3527 0.0878 -0.3569 0.0682 -0.3619 0.0484 -0.3678 0.0286 -0.3746 0.0092 -0.3821 -0.0098 -0.3903 -0.0278 -0.3989 -0.0446 -0.4077 -0.0597 -0.4162 -0.0725 -0.4241 -0.0826 -0.4306 -0.0891 -0.4352 -0.0916 -0.4371 -0.0893 -0.4356 -0.0814 -0.4299 -0.0671 -0.4191 -0.0456 -0.4024 -0.0162 -0.3789 0.0220 -0.3479 0.0698 -0.3085 0.1280 -0.2598 0.1975 -0.2010 0.2789 -0.1310 0.3729 -0.0489 0.4798 0.0467 0.5990 0.1572 0.7279 0.2867 0.8584 0.4298 0.9678 0.6048 0.9897 0.7804 0.7179 0.9575 -0.5361 0.9585 -4.5916 0.2670 -8.0598 -0.9454 -6.4402 -1.0154 -4.6552 -0.7451 -3.5029 -0.5704 -2.7441 -0.4844 -2.2180 -0.4426 -1.8324 -0.4198 -1.5364 -0.4058 -1.3007 -0.3963 -1.1073 -0.3892 -0.9449 -0.3836 -0.8062 -0.3789 -0.6860 -0.3749 -0.5808 -0.3714 -0.4879 -0.3683 -0.4056 -0.3655 -0.3323 -0.3630 -0.2668 -0.3607 -0.2082 -0.3587 -0.1557 -0.3567 -0.1086 -0.3550 -0.0664 -0.3534 -0.0285 -0.3519 0.0055 -0.3506 0.0360 -0.3493 0.0634 -0.3482 0.0881 -0.3472 0.1104 -0.3463 0.1306 -0.3455 0.1490 -0.3447 0.1659 -0.3441 0.1815 -0.3435 0.1961 -0.3430 0.2100 -0.3426 0.2233 -0.3423 0.2364 -0.3420 0.2496 -0.3418 0.2630 -0.3416 0.2769 -0.3414 0.2918 -0.3413 0.3081 -0.3412 0.3262 -0.3412 0.3468 -0.3411 0.3718 -0.3411 0.4029 -0.3411 0.4382 -0.3411 0.5708 -0.3411 -0.8061 -0.3411 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -10.000 0.097 -0.112 -0.038 1.000 1.000 0.0000 -1.0278 Cpi Cpv ----------------- -0.8096 -0.3269 -0.6440 -0.3269 0.4161 -0.3269 0.3925 -0.3269 0.3657 -0.3269 0.3436 -0.3269 0.3225 -0.3269 0.3026 -0.3269 0.2838 -0.3270 0.2655 -0.3271 0.2478 -0.3273 0.2302 -0.3277 0.2126 -0.3284 0.1949 -0.3293 0.1770 -0.3306 0.1587 -0.3324 0.1400 -0.3348 0.1209 -0.3379 0.1013 -0.3417 0.0813 -0.3464 0.0610 -0.3520 0.0405 -0.3584 0.0199 -0.3658 -0.0004 -0.3740 -0.0204 -0.3830 -0.0395 -0.3925 -0.0574 -0.4022 -0.0737 -0.4118 -0.0878 -0.4209 -0.0993 -0.4287 -0.1074 -0.4348 -0.1114 -0.4382 -0.1108 -0.4383 -0.1046 -0.4343 -0.0922 -0.4252 -0.0726 -0.4103 -0.0451 -0.3888 -0.0089 -0.3596 0.0370 -0.3221 0.0933 -0.2753 0.1610 -0.2183 0.2408 -0.1502 0.3335 -0.0698 0.4398 0.0243 0.5593 0.1335 0.6905 0.2620 0.8267 0.4048 0.9487 0.5812 0.9980 0.7600 0.7893 0.9470 -0.3094 0.9694 -4.0208 0.3129 -7.3580 -0.9121 -5.9762 -1.0278 -4.3586 -0.7692 -3.2998 -0.5822 -2.5966 -0.4844 -2.1059 -0.4361 -1.7444 -0.4099 -1.4657 -0.3942 -1.2427 -0.3838 -1.0591 -0.3762 -0.9044 -0.3703 -0.7718 -0.3655 -0.6566 -0.3614 -0.5556 -0.3578 -0.4662 -0.3547 -0.3868 -0.3518 -0.3159 -0.3493 -0.2525 -0.3470 -0.1957 -0.3448 -0.1448 -0.3429 -0.0991 -0.3411 -0.0581 -0.3395 -0.0213 -0.3380 0.0117 -0.3366 0.0414 -0.3354 0.0681 -0.3342 0.0921 -0.3332 0.1138 -0.3322 0.1335 -0.3314 0.1514 -0.3307 0.1678 -0.3300 0.1830 -0.3294 0.1972 -0.3289 0.2108 -0.3285 0.2238 -0.3281 0.2367 -0.3278 0.2496 -0.3276 0.2627 -0.3274 0.2765 -0.3272 0.2912 -0.3271 0.3073 -0.3270 0.3253 -0.3270 0.3458 -0.3269 0.3708 -0.3269 0.4019 -0.3269 0.4372 -0.3269 0.5700 -0.3269 -0.8096 -0.3269 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -9.500 0.093 -0.097 -0.040 1.000 1.000 0.0000 -1.0375 Cpi Cpv ----------------- -0.8129 -0.3128 -0.6470 -0.3128 0.4150 -0.3128 0.3913 -0.3128 0.3644 -0.3129 0.3422 -0.3129 0.3210 -0.3129 0.3009 -0.3130 0.2819 -0.3132 0.2634 -0.3134 0.2454 -0.3138 0.2275 -0.3144 0.2096 -0.3152 0.1916 -0.3164 0.1733 -0.3180 0.1546 -0.3201 0.1354 -0.3229 0.1158 -0.3263 0.0956 -0.3305 0.0750 -0.3356 0.0540 -0.3416 0.0327 -0.3486 0.0113 -0.3565 -0.0100 -0.3653 -0.0308 -0.3750 -0.0510 -0.3853 -0.0701 -0.3960 -0.0876 -0.4067 -0.1031 -0.4169 -0.1160 -0.4261 -0.1256 -0.4335 -0.1313 -0.4385 -0.1323 -0.4403 -0.1279 -0.4379 -0.1174 -0.4307 -0.0998 -0.4176 -0.0743 -0.3979 -0.0401 -0.3706 0.0037 -0.3350 0.0580 -0.2902 0.1237 -0.2351 0.2018 -0.1689 0.2930 -0.0902 0.3983 0.0022 0.5179 0.1100 0.6507 0.2375 0.7918 0.3799 0.9251 0.5574 0.9998 0.7392 0.8503 0.9357 -0.1006 0.9785 -3.4801 0.3571 -6.6833 -0.8768 -5.5261 -1.0375 -4.0691 -0.7952 -3.1008 -0.5979 -2.4516 -0.4879 -1.9954 -0.4317 -1.6574 -0.4014 -1.3955 -0.3834 -1.1851 -0.3718 -1.0111 -0.3636 -0.8640 -0.3573 -0.7375 -0.3523 -0.6273 -0.3480 -0.5303 -0.3444 -0.4444 -0.3412 -0.3679 -0.3383 -0.2995 -0.3357 -0.2382 -0.3334 -0.1832 -0.3312 -0.1339 -0.3292 -0.0895 -0.3274 -0.0497 -0.3258 -0.0140 -0.3242 0.0181 -0.3228 0.0470 -0.3216 0.0729 -0.3204 0.0963 -0.3193 0.1174 -0.3184 0.1365 -0.3175 0.1539 -0.3167 0.1698 -0.3161 0.1847 -0.3155 0.1985 -0.3149 0.2117 -0.3145 0.2245 -0.3141 0.2370 -0.3138 0.2497 -0.3136 0.2626 -0.3134 0.2761 -0.3132 0.2907 -0.3131 0.3066 -0.3130 0.3246 -0.3129 0.3449 -0.3129 0.3698 -0.3129 0.4009 -0.3129 0.4362 -0.3128 0.5692 -0.3128 -0.8129 -0.3128 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -9.000 0.089 -0.083 -0.042 1.000 1.000 0.0000 -1.0442 Cpi Cpv ----------------- -0.8159 -0.2989 -0.6498 -0.2989 0.4140 -0.2989 0.3902 -0.2990 0.3632 -0.2990 0.3409 -0.2990 0.3195 -0.2991 0.2992 -0.2993 0.2800 -0.2995 0.2613 -0.2998 0.2431 -0.3003 0.2249 -0.3011 0.2067 -0.3021 0.1883 -0.3035 0.1697 -0.3053 0.1505 -0.3077 0.1309 -0.3108 0.1107 -0.3145 0.0900 -0.3190 0.0687 -0.3245 0.0471 -0.3309 0.0250 -0.3383 0.0028 -0.3467 -0.0194 -0.3561 -0.0412 -0.3665 -0.0625 -0.3776 -0.0827 -0.3891 -0.1015 -0.4008 -0.1183 -0.4122 -0.1326 -0.4227 -0.1438 -0.4315 -0.1511 -0.4381 -0.1539 -0.4415 -0.1513 -0.4408 -0.1427 -0.4354 -0.1271 -0.4242 -0.1037 -0.4064 -0.0716 -0.3811 -0.0300 -0.3474 0.0222 -0.3045 0.0858 -0.2514 0.1619 -0.1870 0.2515 -0.1102 0.3555 -0.0195 0.4746 0.0869 0.6086 0.2131 0.7538 0.3550 0.8971 0.5334 0.9951 0.7179 0.9009 0.9234 0.0903 0.9860 -2.9695 0.3997 -6.0359 -0.8398 -5.0900 -1.0442 -3.7870 -0.8215 -2.9058 -0.6176 -2.3090 -0.4953 -1.8864 -0.4299 -1.5714 -0.3945 -1.3260 -0.3738 -1.1279 -0.3606 -0.9634 -0.3515 -0.8238 -0.3447 -0.7033 -0.3394 -0.5980 -0.3350 -0.5051 -0.3312 -0.4225 -0.3279 -0.3489 -0.3250 -0.2829 -0.3224 -0.2237 -0.3200 -0.1706 -0.3178 -0.1228 -0.3158 -0.0798 -0.3139 -0.0412 -0.3122 -0.0065 -0.3107 0.0246 -0.3092 0.0527 -0.3079 0.0779 -0.3067 0.1005 -0.3056 0.1210 -0.3047 0.1396 -0.3038 0.1565 -0.3030 0.1720 -0.3023 0.1864 -0.3017 0.1999 -0.3011 0.2128 -0.3007 0.2252 -0.3003 0.2375 -0.3000 0.2499 -0.2997 0.2626 -0.2995 0.2759 -0.2993 0.2903 -0.2992 0.3061 -0.2991 0.3239 -0.2990 0.3442 -0.2990 0.3690 -0.2990 0.4001 -0.2990 0.4354 -0.2990 0.5685 -0.2989 -0.8159 -0.2989 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -8.500 0.085 -0.070 -0.043 1.000 1.000 0.0000 -1.0485 Cpi Cpv ----------------- -0.8187 -0.2852 -0.6523 -0.2852 0.4131 -0.2852 0.3892 -0.2852 0.3621 -0.2853 0.3396 -0.2853 0.3181 -0.2854 0.2977 -0.2856 0.2783 -0.2859 0.2594 -0.2863 0.2409 -0.2870 0.2225 -0.2878 0.2039 -0.2890 0.1852 -0.2906 0.1662 -0.2927 0.1466 -0.2953 0.1265 -0.2985 0.1058 -0.3025 0.0845 -0.3073 0.0626 -0.3130 0.0403 -0.3197 0.0175 -0.3275 -0.0056 -0.3364 -0.0286 -0.3463 -0.0515 -0.3572 -0.0738 -0.3690 -0.0952 -0.3815 -0.1153 -0.3942 -0.1334 -0.4067 -0.1492 -0.4184 -0.1619 -0.4287 -0.1709 -0.4368 -0.1754 -0.4418 -0.1748 -0.4429 -0.1681 -0.4393 -0.1546 -0.4299 -0.1333 -0.4141 -0.1034 -0.3907 -0.0640 -0.3591 -0.0141 -0.3181 0.0473 -0.2670 0.1212 -0.2046 0.2088 -0.1297 0.3113 -0.0407 0.4296 0.0642 0.5641 0.1891 0.7125 0.3303 0.8647 0.5094 0.9838 0.6963 0.9411 0.9103 0.2631 0.9917 -2.4892 0.4402 -5.4160 -0.8014 -4.6681 -1.0485 -3.5122 -0.8475 -2.7151 -0.6413 -2.1689 -0.5074 -1.7790 -0.4314 -1.4865 -0.3898 -1.2572 -0.3655 -1.0712 -0.3503 -0.9160 -0.3400 -0.7837 -0.3326 -0.6692 -0.3269 -0.5687 -0.3222 -0.4798 -0.3183 -0.4006 -0.3149 -0.3298 -0.3119 -0.2663 -0.3092 -0.2092 -0.3068 -0.1578 -0.3045 -0.1116 -0.3025 -0.0700 -0.3006 -0.0326 -0.2989 0.0011 -0.2973 0.0313 -0.2958 0.0585 -0.2945 0.0829 -0.2933 0.1049 -0.2921 0.1248 -0.2911 0.1428 -0.2902 0.1593 -0.2894 0.1743 -0.2887 0.1883 -0.2880 0.2014 -0.2875 0.2139 -0.2870 0.2260 -0.2866 0.2380 -0.2863 0.2502 -0.2860 0.2626 -0.2858 0.2758 -0.2856 0.2900 -0.2855 0.3056 -0.2854 0.3233 -0.2853 0.3435 -0.2853 0.3683 -0.2852 0.3993 -0.2852 0.4346 -0.2852 0.5679 -0.2852 -0.8187 -0.2852 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -8.000 0.081 -0.058 -0.045 1.000 1.000 0.0000 -1.0507 Cpi Cpv ----------------- -0.8211 -0.2717 -0.6546 -0.2717 0.4122 -0.2717 0.3883 -0.2717 0.3611 -0.2717 0.3385 -0.2718 0.3168 -0.2719 0.2963 -0.2722 0.2767 -0.2725 0.2576 -0.2730 0.2388 -0.2737 0.2201 -0.2747 0.2013 -0.2760 0.1822 -0.2777 0.1628 -0.2799 0.1428 -0.2827 0.1222 -0.2861 0.1010 -0.2903 0.0792 -0.2953 0.0566 -0.3012 0.0336 -0.3082 0.0100 -0.3162 -0.0138 -0.3254 -0.0378 -0.3358 -0.0617 -0.3472 -0.0851 -0.3597 -0.1076 -0.3729 -0.1289 -0.3865 -0.1485 -0.4002 -0.1657 -0.4132 -0.1800 -0.4249 -0.1907 -0.4345 -0.1970 -0.4412 -0.1983 -0.4441 -0.1936 -0.4422 -0.1822 -0.4348 -0.1632 -0.4209 -0.1356 -0.3995 -0.0985 -0.3699 -0.0510 -0.3310 0.0080 -0.2819 0.0797 -0.2214 0.1651 -0.1484 0.2658 -0.0613 0.3829 0.0420 0.5173 0.1655 0.6682 0.3060 0.8278 0.4855 0.9660 0.6745 0.9709 0.8965 0.4178 0.9959 -2.0393 0.4785 -4.8237 -0.7617 -4.2606 -1.0507 -3.2448 -0.8718 -2.5286 -0.6685 -2.0314 -0.5243 -1.6733 -0.4371 -1.4026 -0.3878 -1.1891 -0.3591 -1.0149 -0.3413 -0.8689 -0.3295 -0.7439 -0.3212 -0.6351 -0.3149 -0.5395 -0.3099 -0.4545 -0.3058 -0.3787 -0.3022 -0.3107 -0.2991 -0.2496 -0.2964 -0.1946 -0.2938 -0.1450 -0.2916 -0.1003 -0.2895 -0.0601 -0.2876 -0.0238 -0.2858 0.0088 -0.2842 0.0381 -0.2826 0.0644 -0.2813 0.0881 -0.2800 0.1095 -0.2788 0.1287 -0.2778 0.1462 -0.2768 0.1621 -0.2760 0.1767 -0.2753 0.1903 -0.2746 0.2030 -0.2740 0.2152 -0.2735 0.2270 -0.2731 0.2387 -0.2728 0.2506 -0.2725 0.2628 -0.2723 0.2758 -0.2721 0.2898 -0.2719 0.3053 -0.2718 0.3228 -0.2718 0.3429 -0.2717 0.3676 -0.2717 0.3986 -0.2717 0.4339 -0.2717 0.5673 -0.2717 -0.8211 -0.2717 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -7.500 0.078 -0.047 -0.046 1.000 1.000 0.0000 -1.0516 Cpi Cpv ----------------- -0.8233 -0.2583 -0.6566 -0.2583 0.4115 -0.2583 0.3875 -0.2583 0.3602 -0.2584 0.3375 -0.2584 0.3157 -0.2586 0.2950 -0.2589 0.2752 -0.2592 0.2558 -0.2598 0.2368 -0.2606 0.2179 -0.2616 0.1988 -0.2630 0.1794 -0.2649 0.1595 -0.2672 0.1391 -0.2700 0.1181 -0.2736 0.0964 -0.2778 0.0739 -0.2830 0.0508 -0.2890 0.0270 -0.2961 0.0027 -0.3044 -0.0220 -0.3138 -0.0469 -0.3245 -0.0717 -0.3364 -0.0962 -0.3494 -0.1199 -0.3633 -0.1425 -0.3779 -0.1635 -0.3926 -0.1822 -0.4068 -0.1981 -0.4199 -0.2105 -0.4311 -0.2187 -0.4395 -0.2219 -0.4441 -0.2193 -0.4442 -0.2100 -0.4387 -0.1932 -0.4267 -0.1680 -0.4074 -0.1333 -0.3798 -0.0883 -0.3429 -0.0318 -0.2959 0.0373 -0.2375 0.1204 -0.1664 0.2189 -0.0811 0.3343 0.0204 0.4683 0.1424 0.6207 0.2821 0.7866 0.4619 0.9417 0.6527 0.9903 0.8822 0.5544 0.9986 -1.6201 0.5143 -4.2592 -0.7204 -3.8675 -1.0516 -2.9851 -0.8934 -2.3463 -0.6977 -1.8964 -0.5459 -1.5692 -0.4478 -1.3198 -0.3895 -1.1217 -0.3552 -0.9591 -0.3340 -0.8221 -0.3202 -0.7042 -0.3106 -0.6012 -0.3036 -0.5103 -0.2981 -0.4293 -0.2937 -0.3567 -0.2899 -0.2915 -0.2867 -0.2328 -0.2838 -0.1798 -0.2812 -0.1320 -0.2789 -0.0889 -0.2767 -0.0500 -0.2748 -0.0150 -0.2729 0.0166 -0.2713 0.0450 -0.2697 0.0705 -0.2683 0.0934 -0.2670 0.1141 -0.2658 0.1328 -0.2647 0.1497 -0.2637 0.1651 -0.2628 0.1793 -0.2620 0.1925 -0.2614 0.2048 -0.2608 0.2166 -0.2602 0.2281 -0.2598 0.2395 -0.2594 0.2511 -0.2591 0.2631 -0.2589 0.2759 -0.2587 0.2897 -0.2586 0.3051 -0.2585 0.3225 -0.2584 0.3424 -0.2584 0.3671 -0.2583 0.3980 -0.2583 0.4333 -0.2583 0.5668 -0.2583 -0.8233 -0.2583 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -7.000 0.074 -0.038 -0.047 1.000 1.000 0.0000 -1.0540 Cpi Cpv ----------------- -0.8252 -0.2451 -0.6584 -0.2451 0.4108 -0.2451 0.3868 -0.2451 0.3594 -0.2451 0.3365 -0.2452 0.3146 -0.2454 0.2937 -0.2457 0.2738 -0.2461 0.2542 -0.2467 0.2350 -0.2475 0.2158 -0.2486 0.1963 -0.2500 0.1766 -0.2519 0.1564 -0.2543 0.1356 -0.2572 0.1141 -0.2608 0.0918 -0.2651 0.0688 -0.2702 0.0451 -0.2763 0.0206 -0.2835 -0.0045 -0.2918 -0.0300 -0.3014 -0.0558 -0.3122 -0.0816 -0.3244 -0.1072 -0.3379 -0.1322 -0.3525 -0.1560 -0.3679 -0.1784 -0.3836 -0.1986 -0.3991 -0.2161 -0.4136 -0.2303 -0.4264 -0.2403 -0.4365 -0.2455 -0.4429 -0.2450 -0.4449 -0.2379 -0.4413 -0.2234 -0.4314 -0.2006 -0.4141 -0.1685 -0.3886 -0.1261 -0.3538 -0.0723 -0.3088 -0.0058 -0.2525 0.0746 -0.1835 0.1706 -0.1001 0.2841 -0.0003 0.4169 0.1201 0.5701 0.2588 0.7409 0.4386 0.9108 0.6310 0.9993 0.8675 0.6728 0.9999 -1.2316 0.5463 -3.7227 -0.6750 -3.4889 -1.0540 -2.7329 -0.9110 -2.1684 -0.7274 -1.7642 -0.5719 -1.4667 -0.4639 -1.2380 -0.3955 -1.0550 -0.3543 -0.9038 -0.3289 -0.7756 -0.3124 -0.6647 -0.3012 -0.5674 -0.2931 -0.4811 -0.2870 -0.4040 -0.2821 -0.3347 -0.2781 -0.2723 -0.2746 -0.2159 -0.2716 -0.1650 -0.2689 -0.1190 -0.2665 -0.0774 -0.2642 -0.0398 -0.2622 -0.0060 -0.2603 0.0245 -0.2586 0.0520 -0.2570 0.0767 -0.2555 0.0989 -0.2541 0.1189 -0.2529 0.1370 -0.2517 0.1533 -0.2507 0.1683 -0.2498 0.1820 -0.2490 0.1947 -0.2483 0.2067 -0.2476 0.2182 -0.2471 0.2293 -0.2466 0.2404 -0.2463 0.2518 -0.2459 0.2636 -0.2457 0.2761 -0.2455 0.2897 -0.2454 0.3049 -0.2452 0.3222 -0.2452 0.3421 -0.2451 0.3666 -0.2451 0.3975 -0.2451 0.4327 -0.2451 0.5664 -0.2451 -0.8252 -0.2451 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -6.500 0.070 -0.031 -0.047 1.000 1.000 0.0000 -1.0668 Cpi Cpv ----------------- -0.8269 -0.2318 -0.6599 -0.2318 0.4102 -0.2318 0.3861 -0.2319 0.3587 -0.2319 0.3357 -0.2320 0.3137 -0.2322 0.2926 -0.2325 0.2725 -0.2329 0.2527 -0.2335 0.2333 -0.2343 0.2138 -0.2355 0.1940 -0.2369 0.1740 -0.2388 0.1534 -0.2412 0.1321 -0.2441 0.1102 -0.2476 0.0874 -0.2519 0.0638 -0.2570 0.0395 -0.2630 0.0143 -0.2701 -0.0115 -0.2783 -0.0379 -0.2879 -0.0646 -0.2988 -0.0915 -0.3112 -0.1181 -0.3250 -0.1443 -0.3401 -0.1694 -0.3563 -0.1932 -0.3730 -0.2149 -0.3897 -0.2341 -0.4056 -0.2500 -0.4200 -0.2619 -0.4318 -0.2691 -0.4401 -0.2707 -0.4440 -0.2659 -0.4425 -0.2539 -0.4346 -0.2336 -0.4194 -0.2041 -0.3960 -0.1644 -0.3633 -0.1134 -0.3205 -0.0498 -0.2662 0.0278 -0.1992 0.1211 -0.1178 0.2321 -0.0197 0.3632 0.0980 0.5164 0.2402 0.6909 0.4110 0.8735 0.6178 0.9979 0.8433 0.7730 0.9998 -0.8740 0.5495 -3.2145 -0.6014 -3.1250 -1.0668 -2.4884 -0.9211 -1.9949 -0.7567 -1.6346 -0.6018 -1.3660 -0.4856 -1.1575 -0.4071 -0.9891 -0.3576 -0.8490 -0.3267 -0.7294 -0.3067 -0.6254 -0.2933 -0.5337 -0.2838 -0.4520 -0.2767 -0.3787 -0.2712 -0.3127 -0.2667 -0.2530 -0.2630 -0.1990 -0.2597 -0.1501 -0.2569 -0.1058 -0.2543 -0.0658 -0.2519 -0.0295 -0.2498 0.0031 -0.2478 0.0326 -0.2460 0.0591 -0.2443 0.0830 -0.2428 0.1044 -0.2414 0.1238 -0.2401 0.1412 -0.2389 0.1571 -0.2378 0.1715 -0.2369 0.1847 -0.2360 0.1971 -0.2352 0.2087 -0.2346 0.2198 -0.2340 0.2306 -0.2335 0.2415 -0.2331 0.2526 -0.2328 0.2641 -0.2325 0.2764 -0.2323 0.2899 -0.2322 0.3049 -0.2320 0.3220 -0.2320 0.3418 -0.2319 0.3663 -0.2319 0.3971 -0.2319 0.4323 -0.2318 0.5660 -0.2318 -0.8269 -0.2318 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -6.000 0.067 -0.027 -0.048 1.000 1.000 0.0000 -1.0580 Cpi Cpv ----------------- -0.8282 -0.2188 -0.6612 -0.2188 0.4098 -0.2188 0.3856 -0.2188 0.3580 -0.2189 0.3350 -0.2190 0.3128 -0.2191 0.2916 -0.2194 0.2713 -0.2198 0.2514 -0.2204 0.2317 -0.2213 0.2119 -0.2224 0.1919 -0.2238 0.1715 -0.2257 0.1505 -0.2280 0.1288 -0.2308 0.1064 -0.2342 0.0831 -0.2384 0.0590 -0.2433 0.0340 -0.2491 0.0081 -0.2560 -0.0184 -0.2640 -0.0457 -0.2734 -0.0733 -0.2842 -0.1011 -0.2966 -0.1289 -0.3106 -0.1563 -0.3261 -0.1827 -0.3428 -0.2079 -0.3605 -0.2312 -0.3783 -0.2520 -0.3957 -0.2697 -0.4117 -0.2835 -0.4253 -0.2928 -0.4356 -0.2966 -0.4415 -0.2941 -0.4420 -0.2845 -0.4363 -0.2668 -0.4232 -0.2400 -0.4020 -0.2031 -0.3715 -0.1551 -0.3308 -0.0945 -0.2787 -0.0200 -0.2138 0.0703 -0.1344 0.1785 -0.0382 0.3073 0.0777 0.4596 0.2195 0.6365 0.3878 0.8296 0.5985 0.9860 0.8264 0.8550 0.9988 -0.5473 0.5808 -2.7345 -0.5635 -2.7758 -1.0580 -2.2517 -0.9333 -1.8258 -0.7839 -1.5077 -0.6330 -1.2671 -0.5115 -1.0780 -0.4242 -0.9240 -0.3657 -0.7947 -0.3282 -0.6836 -0.3038 -0.5863 -0.2874 -0.5001 -0.2760 -0.4230 -0.2676 -0.3535 -0.2613 -0.2907 -0.2562 -0.2337 -0.2520 -0.1820 -0.2484 -0.1351 -0.2453 -0.0926 -0.2426 -0.0540 -0.2401 -0.0192 -0.2378 0.0123 -0.2357 0.0407 -0.2338 0.0663 -0.2321 0.0894 -0.2304 0.1101 -0.2289 0.1288 -0.2276 0.1457 -0.2263 0.1609 -0.2252 0.1749 -0.2241 0.1876 -0.2232 0.1996 -0.2224 0.2108 -0.2217 0.2216 -0.2211 0.2321 -0.2206 0.2426 -0.2202 0.2534 -0.2198 0.2647 -0.2195 0.2768 -0.2193 0.2901 -0.2191 0.3050 -0.2190 0.3220 -0.2189 0.3416 -0.2189 0.3660 -0.2188 0.3968 -0.2188 0.4319 -0.2188 0.5657 -0.2188 -0.8282 -0.2188 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -5.500 0.064 -0.025 -0.047 1.000 1.000 0.0000 -1.0482 Cpi Cpv ----------------- -0.8293 -0.2057 -0.6622 -0.2057 0.4094 -0.2057 0.3852 -0.2057 0.3575 -0.2058 0.3344 -0.2059 0.3121 -0.2061 0.2907 -0.2063 0.2703 -0.2067 0.2501 -0.2073 0.2302 -0.2081 0.2101 -0.2092 0.1898 -0.2106 0.1691 -0.2123 0.1477 -0.2145 0.1257 -0.2172 0.1028 -0.2204 0.0790 -0.2243 0.0543 -0.2290 0.0286 -0.2345 0.0021 -0.2410 -0.0252 -0.2487 -0.0533 -0.2577 -0.0818 -0.2682 -0.1107 -0.2804 -0.1396 -0.2943 -0.1681 -0.3100 -0.1959 -0.3272 -0.2225 -0.3456 -0.2474 -0.3646 -0.2699 -0.3834 -0.2894 -0.4010 -0.3051 -0.4165 -0.3165 -0.4288 -0.3225 -0.4368 -0.3224 -0.4395 -0.3153 -0.4359 -0.3002 -0.4251 -0.2762 -0.4060 -0.2423 -0.3778 -0.1973 -0.3393 -0.1400 -0.2894 -0.0688 -0.2266 0.0181 -0.1493 0.1231 -0.0551 0.2492 0.0590 0.3998 0.1998 0.5778 0.3665 0.7792 0.5795 0.9637 0.8103 0.9187 0.9969 -0.2516 0.6094 -2.2830 -0.5276 -2.4416 -1.0482 -2.0228 -0.9433 -1.6612 -0.8090 -1.3836 -0.6644 -1.1699 -0.5412 -0.9998 -0.4469 -0.8597 -0.3795 -0.7409 -0.3343 -0.6381 -0.3044 -0.5475 -0.2843 -0.4667 -0.2702 -0.3940 -0.2601 -0.3283 -0.2525 -0.2686 -0.2466 -0.2143 -0.2418 -0.1650 -0.2378 -0.1201 -0.2343 -0.0792 -0.2313 -0.0422 -0.2286 -0.0087 -0.2262 0.0216 -0.2239 0.0490 -0.2219 0.0737 -0.2200 0.0959 -0.2182 0.1159 -0.2166 0.1339 -0.2152 0.1502 -0.2138 0.1649 -0.2126 0.1783 -0.2115 0.1907 -0.2105 0.2022 -0.2096 0.2130 -0.2089 0.2234 -0.2082 0.2336 -0.2077 0.2439 -0.2072 0.2544 -0.2068 0.2655 -0.2065 0.2774 -0.2063 0.2905 -0.2061 0.3052 -0.2060 0.3220 -0.2059 0.3416 -0.2058 0.3658 -0.2058 0.3965 -0.2057 0.4317 -0.2057 0.5655 -0.2057 -0.8293 -0.2057 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -5.000 0.061 -0.027 -0.047 1.000 1.000 0.0000 -1.0382 Cpi Cpv ----------------- -0.8301 -0.1925 -0.6629 -0.1925 0.4091 -0.1925 0.3848 -0.1926 0.3571 -0.1926 0.3338 -0.1927 0.3114 -0.1928 0.2899 -0.1931 0.2693 -0.1935 0.2489 -0.1940 0.2288 -0.1948 0.2085 -0.1958 0.1879 -0.1970 0.1668 -0.1987 0.1451 -0.2007 0.1226 -0.2032 0.0993 -0.2062 0.0750 -0.2098 0.0497 -0.2142 0.0234 -0.2193 -0.0038 -0.2254 -0.0319 -0.2326 -0.0608 -0.2410 -0.0903 -0.2510 -0.1201 -0.2627 -0.1501 -0.2762 -0.1799 -0.2918 -0.2090 -0.3092 -0.2370 -0.3282 -0.2634 -0.3482 -0.2876 -0.3683 -0.3090 -0.3876 -0.3267 -0.4051 -0.3401 -0.4194 -0.3484 -0.4296 -0.3508 -0.4346 -0.3462 -0.4333 -0.3339 -0.4248 -0.3128 -0.4080 -0.2820 -0.3821 -0.2402 -0.3458 -0.1862 -0.2981 -0.1185 -0.2376 -0.0352 -0.1624 0.0661 -0.0702 0.1888 0.0420 0.3369 0.1816 0.5148 0.3468 0.7223 0.5615 0.9310 0.7950 0.9641 0.9945 0.0129 0.6351 -1.8602 -0.4942 -2.1223 -1.0382 -1.8018 -0.9513 -1.5012 -0.8316 -1.2622 -0.6948 -1.0745 -0.5730 -0.9227 -0.4741 -0.7961 -0.3996 -0.6878 -0.3460 -0.5930 -0.3095 -0.5089 -0.2846 -0.4334 -0.2672 -0.3652 -0.2548 -0.3031 -0.2455 -0.2466 -0.2384 -0.1950 -0.2327 -0.1479 -0.2280 -0.1049 -0.2241 -0.0658 -0.2206 -0.0303 -0.2176 0.0019 -0.2149 0.0311 -0.2124 0.0574 -0.2102 0.0812 -0.2081 0.1026 -0.2062 0.1218 -0.2044 0.1392 -0.2028 0.1548 -0.2014 0.1690 -0.2001 0.1819 -0.1989 0.1938 -0.1978 0.2049 -0.1968 0.2153 -0.1960 0.2254 -0.1953 0.2353 -0.1947 0.2452 -0.1942 0.2555 -0.1937 0.2664 -0.1934 0.2780 -0.1931 0.2909 -0.1929 0.3055 -0.1928 0.3222 -0.1927 0.3416 -0.1926 0.3658 -0.1926 0.3964 -0.1926 0.4315 -0.1925 0.5653 -0.1925 -0.8301 -0.1925 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -4.500 0.058 -0.032 -0.046 1.000 1.000 0.0000 -1.0290 Cpi Cpv ----------------- -0.8306 -0.1791 -0.6634 -0.1791 0.4089 -0.1791 0.3845 -0.1791 0.3568 -0.1792 0.3334 -0.1793 0.3109 -0.1794 0.2893 -0.1796 0.2684 -0.1800 0.2479 -0.1805 0.2275 -0.1811 0.2069 -0.1820 0.1860 -0.1832 0.1646 -0.1846 0.1426 -0.1864 0.1197 -0.1887 0.0959 -0.1914 0.0711 -0.1947 0.0452 -0.1986 0.0184 -0.2033 -0.0096 -0.2090 -0.0384 -0.2156 -0.0682 -0.2234 -0.0986 -0.2326 -0.1295 -0.2435 -0.1605 -0.2564 -0.1915 -0.2715 -0.2220 -0.2887 -0.2515 -0.3080 -0.2794 -0.3287 -0.3054 -0.3501 -0.3285 -0.3711 -0.3483 -0.3905 -0.3639 -0.4071 -0.3745 -0.4196 -0.3792 -0.4269 -0.3773 -0.4280 -0.3678 -0.4219 -0.3497 -0.4075 -0.3220 -0.3839 -0.2836 -0.3500 -0.2332 -0.3046 -0.1693 -0.2462 -0.0899 -0.1732 0.0074 -0.0830 0.1262 0.0273 0.2710 0.1655 0.4474 0.3292 0.6590 0.5451 0.8879 0.7808 0.9912 0.9916 0.2461 0.6576 -1.4660 -0.4644 -1.8182 -1.0290 -1.5888 -0.9584 -1.3457 -0.8522 -1.1437 -0.7234 -0.9810 -0.6055 -0.8469 -0.5051 -0.7335 -0.4249 -0.6351 -0.3643 -0.5484 -0.3203 -0.4706 -0.2896 -0.4004 -0.2679 -0.3364 -0.2523 -0.2780 -0.2408 -0.2245 -0.2320 -0.1755 -0.2250 -0.1307 -0.2194 -0.0897 -0.2147 -0.0524 -0.2107 -0.0183 -0.2072 0.0126 -0.2041 0.0406 -0.2013 0.0659 -0.1988 0.0887 -0.1965 0.1093 -0.1944 0.1279 -0.1924 0.1445 -0.1906 0.1596 -0.1890 0.1732 -0.1875 0.1857 -0.1862 0.1971 -0.1850 0.2077 -0.1839 0.2178 -0.1830 0.2275 -0.1822 0.2371 -0.1815 0.2467 -0.1809 0.2568 -0.1805 0.2673 -0.1801 0.2788 -0.1798 0.2915 -0.1796 0.3059 -0.1794 0.3224 -0.1793 0.3417 -0.1792 0.3658 -0.1792 0.3964 -0.1791 0.4314 -0.1791 0.5652 -0.1791 -0.8306 -0.1791 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -4.000 0.055 -0.041 -0.044 1.000 1.000 0.0000 -1.0222 Cpi Cpv ----------------- -0.8309 -0.1654 -0.6637 -0.1654 0.4088 -0.1654 0.3844 -0.1655 0.3565 -0.1655 0.3331 -0.1656 0.3105 -0.1657 0.2887 -0.1659 0.2677 -0.1662 0.2470 -0.1666 0.2264 -0.1672 0.2055 -0.1679 0.1844 -0.1689 0.1626 -0.1702 0.1402 -0.1718 0.1169 -0.1737 0.0926 -0.1761 0.0673 -0.1789 0.0409 -0.1823 0.0134 -0.1865 -0.0152 -0.1914 -0.0448 -0.1973 -0.0754 -0.2045 -0.1067 -0.2129 -0.1386 -0.2229 -0.1708 -0.2348 -0.2030 -0.2489 -0.2348 -0.2656 -0.2658 -0.2847 -0.2954 -0.3059 -0.3230 -0.3283 -0.3480 -0.3509 -0.3698 -0.3723 -0.3876 -0.3911 -0.4005 -0.4061 -0.4078 -0.4159 -0.4086 -0.4196 -0.4019 -0.4159 -0.3869 -0.4040 -0.3625 -0.3829 -0.3275 -0.3513 -0.2809 -0.3082 -0.2209 -0.2522 -0.1458 -0.1813 -0.0528 -0.0932 0.0614 0.0152 0.2020 0.1519 0.3758 0.3142 0.5893 0.5308 0.8344 0.7683 1.0000 0.9887 0.4481 0.6762 -1.1008 -0.4395 -1.5292 -1.0222 -1.3839 -0.9657 -1.1949 -0.8714 -1.0281 -0.7503 -0.8893 -0.6373 -0.7723 -0.5381 -0.6716 -0.4548 -0.5831 -0.3886 -0.5041 -0.3379 -0.4326 -0.3005 -0.3674 -0.2735 -0.3077 -0.2539 -0.2529 -0.2394 -0.2025 -0.2283 -0.1561 -0.2197 -0.1135 -0.2127 -0.0745 -0.2070 -0.0388 -0.2022 -0.0063 -0.1980 0.0234 -0.1943 0.0502 -0.1910 0.0745 -0.1881 0.0964 -0.1854 0.1162 -0.1829 0.1340 -0.1807 0.1500 -0.1786 0.1645 -0.1768 0.1775 -0.1751 0.1895 -0.1735 0.2004 -0.1722 0.2107 -0.1710 0.2204 -0.1699 0.2297 -0.1690 0.2390 -0.1682 0.2483 -0.1675 0.2581 -0.1670 0.2684 -0.1666 0.2796 -0.1662 0.2922 -0.1660 0.3064 -0.1658 0.3228 -0.1656 0.3420 -0.1655 0.3659 -0.1655 0.3964 -0.1655 0.4314 -0.1654 0.5652 -0.1654 -0.8309 -0.1654 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -3.500 0.053 -0.056 -0.042 1.000 1.000 0.0000 -1.0192 Cpi Cpv ----------------- -0.8308 -0.1513 -0.6637 -0.1513 0.4087 -0.1513 0.3843 -0.1513 0.3564 -0.1513 0.3329 -0.1514 0.3101 -0.1515 0.2882 -0.1517 0.2671 -0.1519 0.2461 -0.1523 0.2253 -0.1528 0.2043 -0.1534 0.1828 -0.1542 0.1607 -0.1553 0.1380 -0.1566 0.1142 -0.1582 0.0895 -0.1602 0.0637 -0.1626 0.0368 -0.1654 0.0086 -0.1689 -0.0207 -0.1731 -0.0511 -0.1782 -0.0825 -0.1843 -0.1147 -0.1918 -0.1477 -0.2008 -0.1810 -0.2116 -0.2144 -0.2245 -0.2476 -0.2401 -0.2800 -0.2584 -0.3112 -0.2795 -0.3405 -0.3026 -0.3675 -0.3265 -0.3913 -0.3499 -0.4112 -0.3711 -0.4266 -0.3887 -0.4364 -0.4012 -0.4399 -0.4075 -0.4362 -0.4065 -0.4244 -0.3972 -0.4033 -0.3785 -0.3720 -0.3494 -0.3293 -0.3087 -0.2735 -0.2549 -0.2028 -0.1863 -0.1147 -0.1002 -0.0055 0.0063 0.1301 0.1413 0.2999 0.3022 0.5131 0.5191 0.7705 0.7580 0.9905 0.9861 0.6187 0.6906 -0.7645 -0.4212 -1.2555 -1.0192 -1.1870 -0.9745 -1.0488 -0.8904 -0.9154 -0.7761 -0.7995 -0.6682 -0.6990 -0.5717 -0.6107 -0.4880 -0.5317 -0.4181 -0.4602 -0.3621 -0.3948 -0.3184 -0.3347 -0.2855 -0.2792 -0.2609 -0.2279 -0.2425 -0.1805 -0.2285 -0.1367 -0.2175 -0.0963 -0.2087 -0.0592 -0.2015 -0.0252 -0.1954 0.0059 -0.1903 0.0342 -0.1858 0.0599 -0.1818 0.0832 -0.1782 0.1042 -0.1750 0.1232 -0.1720 0.1402 -0.1694 0.1556 -0.1669 0.1694 -0.1647 0.1820 -0.1627 0.1934 -0.1609 0.2039 -0.1593 0.2138 -0.1578 0.2230 -0.1566 0.2321 -0.1555 0.2410 -0.1546 0.2501 -0.1538 0.2595 -0.1531 0.2696 -0.1526 0.2806 -0.1522 0.2930 -0.1519 0.3070 -0.1517 0.3233 -0.1515 0.3423 -0.1514 0.3662 -0.1514 0.3965 -0.1513 0.4315 -0.1513 0.5652 -0.1513 -0.8308 -0.1513 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -3.000 0.051 -0.076 -0.038 1.000 1.000 0.0000 -1.0215 Cpi Cpv ----------------- -0.8305 -0.1363 -0.6634 -0.1363 0.4088 -0.1363 0.3843 -0.1363 0.3564 -0.1363 0.3328 -0.1364 0.3099 -0.1365 0.2879 -0.1366 0.2666 -0.1368 0.2454 -0.1371 0.2244 -0.1375 0.2031 -0.1380 0.1813 -0.1387 0.1590 -0.1396 0.1358 -0.1406 0.1117 -0.1419 0.0865 -0.1435 0.0602 -0.1455 0.0327 -0.1478 0.0040 -0.1506 -0.0260 -0.1540 -0.0572 -0.1582 -0.0894 -0.1633 -0.1226 -0.1695 -0.1565 -0.1773 -0.1910 -0.1868 -0.2257 -0.1985 -0.2602 -0.2125 -0.2941 -0.2295 -0.3269 -0.2498 -0.3580 -0.2729 -0.3868 -0.2978 -0.4127 -0.3229 -0.4349 -0.3465 -0.4527 -0.3668 -0.4651 -0.3822 -0.4714 -0.3914 -0.4707 -0.3932 -0.4621 -0.3866 -0.4446 -0.3705 -0.4171 -0.3439 -0.3784 -0.3056 -0.3270 -0.2542 -0.2611 -0.1877 -0.1782 -0.1037 -0.0746 0.0009 0.0552 0.1344 0.2197 0.2939 0.4305 0.5107 0.6963 0.7504 0.9626 0.9840 0.7579 0.7003 -0.4572 -0.4105 -0.9971 -1.0215 -0.9983 -0.9861 -0.9074 -0.9101 -0.8056 -0.8015 -0.7116 -0.6982 -0.6270 -0.6051 -0.5506 -0.5227 -0.4809 -0.4515 -0.4168 -0.3918 -0.3574 -0.3434 -0.3022 -0.3048 -0.2508 -0.2747 -0.2030 -0.2516 -0.1585 -0.2337 -0.1172 -0.2196 -0.0790 -0.2083 -0.0438 -0.1990 -0.0115 -0.1913 0.0181 -0.1847 0.0452 -0.1790 0.0697 -0.1739 0.0920 -0.1694 0.1121 -0.1654 0.1303 -0.1618 0.1466 -0.1585 0.1613 -0.1555 0.1745 -0.1527 0.1865 -0.1503 0.1975 -0.1480 0.2075 -0.1460 0.2169 -0.1443 0.2258 -0.1427 0.2345 -0.1414 0.2431 -0.1403 0.2519 -0.1393 0.2611 -0.1385 0.2709 -0.1379 0.2817 -0.1374 0.2939 -0.1370 0.3077 -0.1368 0.3238 -0.1366 0.3427 -0.1365 0.3665 -0.1364 0.3968 -0.1363 0.4316 -0.1363 0.5653 -0.1363 -0.8305 -0.1363 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -2.500 0.049 -0.103 -0.034 1.000 1.000 0.0000 -1.0298 Cpi Cpv ----------------- -0.8299 -0.1201 -0.6629 -0.1201 0.4090 -0.1201 0.3845 -0.1201 0.3564 -0.1201 0.3327 -0.1201 0.3098 -0.1202 0.2876 -0.1203 0.2662 -0.1205 0.2449 -0.1207 0.2236 -0.1210 0.2020 -0.1214 0.1800 -0.1220 0.1573 -0.1226 0.1338 -0.1235 0.1093 -0.1245 0.0837 -0.1258 0.0569 -0.1273 0.0288 -0.1291 -0.0006 -0.1313 -0.0312 -0.1340 -0.0631 -0.1374 -0.0962 -0.1414 -0.1303 -0.1465 -0.1653 -0.1528 -0.2009 -0.1608 -0.2368 -0.1708 -0.2726 -0.1833 -0.3080 -0.1986 -0.3424 -0.2172 -0.3754 -0.2395 -0.4061 -0.2647 -0.4341 -0.2913 -0.4586 -0.3171 -0.4788 -0.3402 -0.4939 -0.3586 -0.5030 -0.3709 -0.5054 -0.3757 -0.5001 -0.3720 -0.4862 -0.3586 -0.4626 -0.3346 -0.4281 -0.2988 -0.3814 -0.2496 -0.3206 -0.1853 -0.2433 -0.1035 -0.1458 -0.0006 -0.0226 0.1312 0.1354 0.2894 0.3416 0.5058 0.6117 0.7458 0.9165 0.9827 0.8657 0.7053 -0.1792 -0.4082 -0.7541 -1.0298 -0.8178 -1.0011 -0.7708 -0.9312 -0.6988 -0.8269 -0.6257 -0.7275 -0.5563 -0.6376 -0.4914 -0.5575 -0.4307 -0.4867 -0.3738 -0.4255 -0.3202 -0.3738 -0.2698 -0.3310 -0.2225 -0.2960 -0.1781 -0.2678 -0.1365 -0.2453 -0.0978 -0.2273 -0.0618 -0.2127 -0.0284 -0.2007 0.0023 -0.1906 0.0304 -0.1820 0.0562 -0.1745 0.0796 -0.1680 0.1009 -0.1622 0.1201 -0.1570 0.1374 -0.1523 0.1530 -0.1481 0.1671 -0.1442 0.1797 -0.1407 0.1912 -0.1376 0.2016 -0.1348 0.2112 -0.1323 0.2202 -0.1300 0.2287 -0.1281 0.2371 -0.1264 0.2454 -0.1250 0.2538 -0.1238 0.2628 -0.1228 0.2724 -0.1221 0.2829 -0.1214 0.2949 -0.1210 0.3085 -0.1206 0.3245 -0.1204 0.3432 -0.1202 0.3669 -0.1201 0.3971 -0.1201 0.4319 -0.1201 0.5655 -0.1201 -0.8299 -0.1201 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -2.000 0.046 -0.134 -0.029 1.000 1.000 0.0000 -1.0426 Cpi Cpv ----------------- -0.8290 -0.1025 -0.6621 -0.1025 0.4092 -0.1025 0.3847 -0.1025 0.3566 -0.1025 0.3328 -0.1025 0.3098 -0.1026 0.2875 -0.1027 0.2659 -0.1028 0.2444 -0.1030 0.2229 -0.1032 0.2011 -0.1036 0.1788 -0.1040 0.1558 -0.1045 0.1320 -0.1051 0.1070 -0.1059 0.0810 -0.1069 0.0537 -0.1080 0.0251 -0.1094 -0.0049 -0.1112 -0.0363 -0.1132 -0.0689 -0.1158 -0.1029 -0.1189 -0.1379 -0.1229 -0.1739 -0.1279 -0.2106 -0.1342 -0.2478 -0.1424 -0.2850 -0.1530 -0.3219 -0.1665 -0.3579 -0.1831 -0.3926 -0.2037 -0.4253 -0.2282 -0.4554 -0.2554 -0.4822 -0.2831 -0.5049 -0.3090 -0.5227 -0.3306 -0.5348 -0.3461 -0.5403 -0.3542 -0.5384 -0.3535 -0.5282 -0.3430 -0.5086 -0.3217 -0.4785 -0.2884 -0.4367 -0.2417 -0.3813 -0.1796 -0.3099 -0.0998 -0.2192 0.0012 -0.1033 0.1313 0.0468 0.2882 0.2463 0.5039 0.5168 0.7438 0.8521 0.9821 0.9419 0.7065 0.0697 -0.4124 -0.5267 -1.0426 -0.6457 -1.0185 -0.6390 -0.9529 -0.5950 -0.8518 -0.5417 -0.7555 -0.4870 -0.6684 -0.4332 -0.5906 -0.3812 -0.5214 -0.3312 -0.4603 -0.2834 -0.4071 -0.2377 -0.3615 -0.1943 -0.3231 -0.1533 -0.2910 -0.1146 -0.2640 -0.0783 -0.2417 -0.0445 -0.2232 -0.0130 -0.2076 0.0161 -0.1945 0.0428 -0.1832 0.0673 -0.1733 0.0896 -0.1647 0.1099 -0.1570 0.1282 -0.1501 0.1447 -0.1440 0.1596 -0.1384 0.1730 -0.1333 0.1851 -0.1288 0.1960 -0.1247 0.2059 -0.1210 0.2151 -0.1178 0.2236 -0.1149 0.2318 -0.1124 0.2398 -0.1103 0.2477 -0.1085 0.2559 -0.1071 0.2646 -0.1059 0.2739 -0.1049 0.2842 -0.1042 0.2960 -0.1036 0.3094 -0.1032 0.3252 -0.1029 0.3439 -0.1027 0.3674 -0.1026 0.3975 -0.1025 0.4322 -0.1025 0.5657 -0.1025 -0.8290 -0.1025 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -1.500 0.044 -0.157 -0.025 1.000 1.000 0.0000 -1.0300 Cpi Cpv ----------------- -0.8279 -0.0885 -0.6611 -0.0885 0.4095 -0.0885 0.3850 -0.0885 0.3568 -0.0886 0.3330 -0.0886 0.3099 -0.0886 0.2875 -0.0887 0.2657 -0.0888 0.2440 -0.0889 0.2224 -0.0891 0.2003 -0.0894 0.1777 -0.0897 0.1544 -0.0901 0.1302 -0.0906 0.1049 -0.0912 0.0784 -0.0919 0.0506 -0.0928 0.0214 -0.0939 -0.0092 -0.0952 -0.0412 -0.0968 -0.0746 -0.0987 -0.1094 -0.1012 -0.1453 -0.1042 -0.1824 -0.1082 -0.2202 -0.1132 -0.2586 -0.1198 -0.2972 -0.1285 -0.3356 -0.1399 -0.3733 -0.1547 -0.4098 -0.1731 -0.4445 -0.1959 -0.4767 -0.2228 -0.5058 -0.2518 -0.5310 -0.2801 -0.5515 -0.3049 -0.5666 -0.3239 -0.5753 -0.3353 -0.5769 -0.3380 -0.5705 -0.3307 -0.5551 -0.3124 -0.5296 -0.2819 -0.4928 -0.2379 -0.4430 -0.1785 -0.3781 -0.1011 -0.2946 -0.0025 -0.1869 0.1256 -0.0459 0.2805 0.1447 0.4954 0.4117 0.7354 0.7694 0.9793 0.9867 0.7195 0.2891 -0.3903 -0.3148 -1.0300 -0.4818 -1.0151 -0.5121 -0.9572 -0.4942 -0.8614 -0.4598 -0.7695 -0.4190 -0.6863 -0.3759 -0.6116 -0.3323 -0.5449 -0.2891 -0.4854 -0.2468 -0.4326 -0.2058 -0.3862 -0.1663 -0.3460 -0.1286 -0.3112 -0.0927 -0.2815 -0.0589 -0.2559 -0.0271 -0.2339 0.0025 -0.2149 0.0299 -0.1985 0.0553 -0.1842 0.0785 -0.1716 0.0997 -0.1604 0.1190 -0.1505 0.1364 -0.1416 0.1521 -0.1337 0.1663 -0.1266 0.1790 -0.1202 0.1905 -0.1145 0.2009 -0.1095 0.2103 -0.1051 0.2190 -0.1013 0.2272 -0.0981 0.2349 -0.0955 0.2425 -0.0934 0.2502 -0.0919 0.2580 -0.0907 0.2664 -0.0899 0.2755 -0.0894 0.2856 -0.0890 0.2972 -0.0888 0.3105 -0.0887 0.3261 -0.0886 0.3446 -0.0886 0.3680 -0.0886 0.3980 -0.0885 0.4326 -0.0885 0.5660 -0.0885 -0.8279 -0.0885 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -1.000 0.043 -0.135 -0.026 1.000 1.000 0.0000 -0.9303 Cpi Cpv ----------------- -0.8265 -0.0919 -0.6598 -0.0919 0.4100 -0.0919 0.3854 -0.0920 0.3572 -0.0920 0.3333 -0.0920 0.3101 -0.0920 0.2875 -0.0921 0.2656 -0.0922 0.2438 -0.0923 0.2219 -0.0924 0.1996 -0.0927 0.1768 -0.0929 0.1532 -0.0933 0.1286 -0.0937 0.1029 -0.0942 0.0760 -0.0948 0.0477 -0.0956 0.0180 -0.0965 -0.0133 -0.0976 -0.0459 -0.0989 -0.0801 -0.1005 -0.1157 -0.1026 -0.1526 -0.1051 -0.1907 -0.1084 -0.2297 -0.1126 -0.2693 -0.1182 -0.3093 -0.1256 -0.3491 -0.1355 -0.3885 -0.1487 -0.4268 -0.1656 -0.4635 -0.1868 -0.4979 -0.2128 -0.5293 -0.2422 -0.5571 -0.2724 -0.5804 -0.3000 -0.5985 -0.3224 -0.6105 -0.3376 -0.6157 -0.3440 -0.6132 -0.3404 -0.6020 -0.3258 -0.5813 -0.2991 -0.5498 -0.2589 -0.5060 -0.2033 -0.4478 -0.1299 -0.3720 -0.0353 -0.2734 0.0887 -0.1427 0.2394 0.0368 0.4538 0.2963 0.6956 0.6685 0.9638 0.9999 0.7810 0.4792 -0.2593 -0.1186 -0.9146 -0.3263 -0.9303 -0.3900 -0.8967 -0.3966 -0.8164 -0.3798 -0.7361 -0.3524 -0.6617 -0.3196 -0.5940 -0.2842 -0.5326 -0.2476 -0.4771 -0.2107 -0.4270 -0.1742 -0.3821 -0.1385 -0.3422 -0.1040 -0.3069 -0.0709 -0.2760 -0.0395 -0.2490 -0.0098 -0.2253 0.0180 -0.2046 0.0438 -0.1865 0.0678 -0.1705 0.0897 -0.1563 0.1098 -0.1438 0.1281 -0.1327 0.1447 -0.1229 0.1596 -0.1143 0.1730 -0.1067 0.1851 -0.1003 0.1960 -0.0950 0.2058 -0.0907 0.2148 -0.0875 0.2230 -0.0852 0.2308 -0.0839 0.2382 -0.0834 0.2454 -0.0836 0.2527 -0.0842 0.2603 -0.0852 0.2684 -0.0864 0.2773 -0.0876 0.2872 -0.0887 0.2985 -0.0896 0.3116 -0.0904 0.3271 -0.0910 0.3454 -0.0914 0.3687 -0.0917 0.3986 -0.0918 0.4331 -0.0919 0.5664 -0.0919 -0.8265 -0.0919 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn -0.500 0.044 -0.098 -0.028 1.000 1.000 0.0000 -0.8112 Cpi Cpv ----------------- -0.8247 -0.1029 -0.6583 -0.1029 0.4105 -0.1029 0.3859 -0.1029 0.3576 -0.1029 0.3337 -0.1030 0.3104 -0.1030 0.2877 -0.1030 0.2657 -0.1031 0.2437 -0.1032 0.2216 -0.1034 0.1991 -0.1036 0.1759 -0.1038 0.1520 -0.1041 0.1271 -0.1045 0.1010 -0.1049 0.0737 -0.1055 0.0449 -0.1061 0.0146 -0.1069 -0.0172 -0.1079 -0.0506 -0.1090 -0.0855 -0.1105 -0.1219 -0.1122 -0.1597 -0.1144 -0.1988 -0.1173 -0.2389 -0.1209 -0.2798 -0.1258 -0.3212 -0.1322 -0.3626 -0.1409 -0.4036 -0.1526 -0.4438 -0.1681 -0.4824 -0.1878 -0.5190 -0.2125 -0.5528 -0.2419 -0.5832 -0.2733 -0.6093 -0.3035 -0.6304 -0.3292 -0.6458 -0.3481 -0.6547 -0.3585 -0.6562 -0.3589 -0.6494 -0.3485 -0.6336 -0.3260 -0.6076 -0.2902 -0.5700 -0.2392 -0.5189 -0.1706 -0.4515 -0.0810 -0.3628 0.0376 -0.2437 0.1830 -0.0773 0.3955 0.1706 0.6383 0.5493 0.9361 0.9816 0.8522 0.6399 -0.0900 0.0620 -0.7581 -0.1792 -0.8112 -0.2729 -0.8078 -0.3020 -0.7464 -0.3020 -0.6805 -0.2872 -0.6171 -0.2643 -0.5578 -0.2367 -0.5029 -0.2065 -0.4523 -0.1748 -0.4060 -0.1428 -0.3639 -0.1108 -0.3258 -0.0795 -0.2916 -0.0491 -0.2611 -0.0201 -0.2341 0.0075 -0.2102 0.0335 -0.1892 0.0578 -0.1706 0.0803 -0.1543 0.1011 -0.1399 0.1201 -0.1273 0.1374 -0.1164 0.1530 -0.1069 0.1672 -0.0988 0.1799 -0.0922 0.1913 -0.0869 0.2016 -0.0830 0.2109 -0.0804 0.2194 -0.0790 0.2272 -0.0788 0.2345 -0.0796 0.2415 -0.0811 0.2484 -0.0833 0.2554 -0.0859 0.2627 -0.0887 0.2705 -0.0915 0.2791 -0.0942 0.2888 -0.0965 0.2999 -0.0984 0.3128 -0.1000 0.3282 -0.1011 0.3464 -0.1019 0.3695 -0.1024 0.3993 -0.1027 0.4337 -0.1028 0.5668 -0.1029 -0.8247 -0.1029 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 0.000 0.044 -0.059 -0.030 1.000 1.000 0.0000 -0.7138 Cpi Cpv ----------------- -0.8228 -0.1156 -0.6565 -0.1156 0.4111 -0.1156 0.3864 -0.1157 0.3582 -0.1157 0.3342 -0.1157 0.3108 -0.1157 0.2880 -0.1158 0.2658 -0.1158 0.2436 -0.1159 0.2214 -0.1161 0.1986 -0.1162 0.1752 -0.1164 0.1510 -0.1167 0.1258 -0.1170 0.0993 -0.1175 0.0715 -0.1179 0.0423 -0.1185 0.0114 -0.1192 -0.0210 -0.1200 -0.0550 -0.1211 -0.0907 -0.1223 -0.1280 -0.1238 -0.1667 -0.1258 -0.2068 -0.1282 -0.2481 -0.1314 -0.2902 -0.1356 -0.3330 -0.1412 -0.3759 -0.1487 -0.4186 -0.1591 -0.4606 -0.1731 -0.5012 -0.1914 -0.5400 -0.2146 -0.5762 -0.2431 -0.6092 -0.2753 -0.6382 -0.3076 -0.6625 -0.3365 -0.6813 -0.3592 -0.6939 -0.3736 -0.6995 -0.3784 -0.6973 -0.3723 -0.6865 -0.3543 -0.6662 -0.3231 -0.6351 -0.2770 -0.5916 -0.2137 -0.5330 -0.1296 -0.4549 -0.0172 -0.3487 0.1222 -0.1976 0.3314 0.0349 0.5734 0.4120 0.8985 0.9318 0.9123 0.7710 0.0763 0.2268 -0.5983 -0.0407 -0.6875 -0.1608 -0.7138 -0.2105 -0.6714 -0.2261 -0.6201 -0.2234 -0.5677 -0.2099 -0.5169 -0.1899 -0.4686 -0.1659 -0.4233 -0.1394 -0.3811 -0.1116 -0.3421 -0.0833 -0.3064 -0.0551 -0.2740 -0.0274 -0.2447 -0.0007 -0.2186 0.0249 -0.1953 0.0491 -0.1746 0.0718 -0.1564 0.0929 -0.1404 0.1125 -0.1265 0.1304 -0.1144 0.1467 -0.1041 0.1615 -0.0954 0.1748 -0.0883 0.1869 -0.0828 0.1977 -0.0789 0.2074 -0.0764 0.2161 -0.0753 0.2241 -0.0756 0.2314 -0.0770 0.2384 -0.0795 0.2450 -0.0827 0.2515 -0.0866 0.2582 -0.0908 0.2652 -0.0951 0.2728 -0.0993 0.2811 -0.1031 0.2905 -0.1065 0.3014 -0.1092 0.3142 -0.1114 0.3293 -0.1131 0.3474 -0.1142 0.3704 -0.1149 0.4001 -0.1153 0.4344 -0.1155 0.5673 -0.1156 -0.8228 -0.1156 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 0.500 0.045 -0.020 -0.031 1.000 1.000 0.0000 -0.6202 Cpi Cpv ----------------- -0.8205 -0.1290 -0.6545 -0.1290 0.4118 -0.1290 0.3871 -0.1290 0.3588 -0.1290 0.3348 -0.1290 0.3113 -0.1291 0.2884 -0.1291 0.2661 -0.1292 0.2438 -0.1293 0.2213 -0.1294 0.1983 -0.1295 0.1747 -0.1297 0.1502 -0.1300 0.1246 -0.1303 0.0977 -0.1306 0.0695 -0.1311 0.0397 -0.1316 0.0084 -0.1322 -0.0246 -0.1329 -0.0593 -0.1338 -0.0958 -0.1349 -0.1339 -0.1362 -0.1735 -0.1379 -0.2147 -0.1400 -0.2571 -0.1428 -0.3005 -0.1464 -0.3446 -0.1513 -0.3890 -0.1578 -0.4334 -0.1669 -0.4772 -0.1793 -0.5199 -0.1961 -0.5609 -0.2176 -0.5996 -0.2448 -0.6352 -0.2769 -0.6671 -0.3109 -0.6946 -0.3428 -0.7169 -0.3693 -0.7333 -0.3879 -0.7431 -0.3970 -0.7456 -0.3955 -0.7400 -0.3822 -0.7256 -0.3559 -0.7013 -0.3150 -0.6657 -0.2572 -0.6165 -0.1790 -0.5498 -0.0734 -0.4578 0.0593 -0.3241 0.2638 -0.1111 0.5030 0.2566 0.8520 0.8505 0.9573 0.8726 0.2308 0.3758 -0.4432 0.0894 -0.5661 -0.0536 -0.6202 -0.1222 -0.5959 -0.1524 -0.5588 -0.1610 -0.5173 -0.1566 -0.4748 -0.1439 -0.4331 -0.1258 -0.3931 -0.1043 -0.3550 -0.0807 -0.3194 -0.0560 -0.2863 -0.0308 -0.2559 -0.0058 -0.2282 0.0186 -0.2033 0.0422 -0.1810 0.0647 -0.1612 0.0858 -0.1437 0.1056 -0.1284 0.1239 -0.1152 0.1407 -0.1039 0.1561 -0.0944 0.1700 -0.0866 0.1826 -0.0806 0.1939 -0.0763 0.2041 -0.0735 0.2132 -0.0724 0.2214 -0.0727 0.2289 -0.0744 0.2358 -0.0773 0.2423 -0.0813 0.2485 -0.0860 0.2548 -0.0914 0.2611 -0.0970 0.2678 -0.1026 0.2751 -0.1080 0.2832 -0.1129 0.2924 -0.1172 0.3031 -0.1208 0.3156 -0.1236 0.3306 -0.1257 0.3485 -0.1271 0.3714 -0.1281 0.4010 -0.1286 0.4352 -0.1288 0.5679 -0.1289 -0.8205 -0.1290 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 1.000 0.047 0.019 -0.032 1.000 1.000 0.0000 -0.5284 Cpi Cpv ----------------- -0.8180 -0.1427 -0.6522 -0.1427 0.4125 -0.1427 0.3879 -0.1427 0.3596 -0.1427 0.3355 -0.1427 0.3119 -0.1428 0.2889 -0.1428 0.2665 -0.1429 0.2440 -0.1429 0.2213 -0.1430 0.1981 -0.1432 0.1742 -0.1434 0.1494 -0.1436 0.1235 -0.1439 0.0963 -0.1442 0.0676 -0.1446 0.0374 -0.1450 0.0055 -0.1456 -0.0281 -0.1462 -0.0635 -0.1470 -0.1007 -0.1479 -0.1396 -0.1491 -0.1802 -0.1505 -0.2223 -0.1524 -0.2659 -0.1547 -0.3105 -0.1579 -0.3560 -0.1620 -0.4020 -0.1677 -0.4481 -0.1755 -0.4938 -0.1864 -0.5385 -0.2014 -0.5818 -0.2214 -0.6229 -0.2468 -0.6612 -0.2782 -0.6960 -0.3131 -0.7267 -0.3476 -0.7525 -0.3778 -0.7728 -0.4007 -0.7870 -0.4144 -0.7942 -0.4176 -0.7941 -0.4092 -0.7858 -0.3880 -0.7685 -0.3525 -0.7412 -0.3006 -0.7020 -0.2287 -0.6475 -0.1303 -0.5709 -0.0048 -0.4568 0.1934 -0.2671 0.4279 0.0830 0.7968 0.7376 0.9863 0.9447 0.3710 0.5089 -0.2951 0.2109 -0.4492 0.0485 -0.5284 -0.0370 -0.5214 -0.0808 -0.4981 -0.1001 -0.4670 -0.1043 -0.4327 -0.0985 -0.3975 -0.0863 -0.3625 -0.0696 -0.3287 -0.0501 -0.2964 -0.0288 -0.2660 -0.0067 -0.2378 0.0157 -0.2120 0.0379 -0.1885 0.0595 -0.1674 0.0802 -0.1487 0.0999 -0.1321 0.1183 -0.1177 0.1354 -0.1053 0.1512 -0.0949 0.1656 -0.0863 0.1786 -0.0796 0.1904 -0.0746 0.2011 -0.0714 0.2106 -0.0698 0.2191 -0.0699 0.2268 -0.0715 0.2338 -0.0745 0.2403 -0.0787 0.2464 -0.0841 0.2522 -0.0902 0.2581 -0.0969 0.2641 -0.1038 0.2705 -0.1107 0.2775 -0.1173 0.2853 -0.1232 0.2943 -0.1284 0.3048 -0.1328 0.3172 -0.1362 0.3320 -0.1387 0.3497 -0.1404 0.3725 -0.1415 0.4019 -0.1422 0.4360 -0.1425 0.5685 -0.1426 -0.8180 -0.1427 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 1.500 0.048 0.056 -0.032 1.000 1.000 0.0000 -0.4486 Cpi Cpv ----------------- -0.8152 -0.1566 -0.6497 -0.1566 0.4134 -0.1566 0.3888 -0.1566 0.3604 -0.1566 0.3363 -0.1566 0.3126 -0.1566 0.2895 -0.1567 0.2670 -0.1567 0.2443 -0.1568 0.2215 -0.1569 0.1981 -0.1570 0.1739 -0.1572 0.1488 -0.1574 0.1226 -0.1576 0.0949 -0.1579 0.0659 -0.1583 0.0352 -0.1587 0.0028 -0.1592 -0.0315 -0.1597 -0.0675 -0.1604 -0.1054 -0.1612 -0.1452 -0.1622 -0.1867 -0.1635 -0.2299 -0.1650 -0.2745 -0.1671 -0.3204 -0.1697 -0.3673 -0.1733 -0.4149 -0.1782 -0.4627 -0.1849 -0.5102 -0.1943 -0.5570 -0.2075 -0.6025 -0.2257 -0.6461 -0.2492 -0.6871 -0.2791 -0.7249 -0.3143 -0.7589 -0.3508 -0.7883 -0.3845 -0.8126 -0.4117 -0.8311 -0.4301 -0.8433 -0.4383 -0.8487 -0.4349 -0.8467 -0.4191 -0.8367 -0.3892 -0.8181 -0.3434 -0.7894 -0.2781 -0.7479 -0.1875 -0.6879 -0.0698 -0.5956 0.1209 -0.4331 0.3488 -0.1085 0.7336 0.5934 0.9993 0.9871 0.4950 0.6262 -0.1532 0.3239 -0.3396 0.1455 -0.4387 0.0449 -0.4486 -0.0113 -0.4386 -0.0407 -0.4176 -0.0530 -0.3911 -0.0540 -0.3621 -0.0473 -0.3322 -0.0353 -0.3024 -0.0197 -0.2735 -0.0019 -0.2459 0.0173 -0.2201 0.0372 -0.1961 0.0572 -0.1742 0.0768 -0.1545 0.0958 -0.1368 0.1140 -0.1214 0.1310 -0.1079 0.1470 -0.0965 0.1617 -0.0870 0.1751 -0.0794 0.1873 -0.0736 0.1984 -0.0697 0.2083 -0.0675 0.2172 -0.0671 0.2252 -0.0683 0.2323 -0.0711 0.2388 -0.0754 0.2448 -0.0809 0.2505 -0.0875 0.2560 -0.0949 0.2615 -0.1028 0.2672 -0.1110 0.2733 -0.1191 0.2800 -0.1268 0.2876 -0.1338 0.2963 -0.1398 0.3066 -0.1449 0.3188 -0.1489 0.3335 -0.1519 0.3511 -0.1539 0.3737 -0.1552 0.4030 -0.1560 0.4370 -0.1563 0.5692 -0.1565 -0.8152 -0.1566 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 2.000 0.050 0.092 -0.033 1.000 1.000 0.0000 -0.4592 Cpi Cpv ----------------- -0.8121 -0.1706 -0.6469 -0.1706 0.4144 -0.1706 0.3897 -0.1706 0.3614 -0.1706 0.3372 -0.1706 0.3134 -0.1706 0.2903 -0.1706 0.2676 -0.1707 0.2448 -0.1708 0.2217 -0.1708 0.1981 -0.1710 0.1737 -0.1711 0.1483 -0.1713 0.1217 -0.1715 0.0938 -0.1718 0.0642 -0.1721 0.0331 -0.1725 0.0002 -0.1729 -0.0347 -0.1734 -0.0714 -0.1740 -0.1100 -0.1747 -0.1506 -0.1755 -0.1930 -0.1766 -0.2372 -0.1779 -0.2830 -0.1797 -0.3302 -0.1819 -0.3785 -0.1850 -0.4276 -0.1892 -0.4770 -0.1949 -0.5265 -0.2030 -0.5753 -0.2144 -0.6231 -0.2305 -0.6692 -0.2522 -0.7130 -0.2801 -0.7538 -0.3145 -0.7911 -0.3524 -0.8242 -0.3892 -0.8525 -0.4207 -0.8755 -0.4440 -0.8927 -0.4572 -0.9038 -0.4592 -0.9084 -0.4488 -0.9060 -0.4248 -0.8964 -0.3853 -0.8787 -0.3271 -0.8511 -0.2448 -0.8089 -0.1321 -0.7404 0.0403 -0.6091 0.2754 -0.3181 0.6518 0.4177 0.9965 0.9999 0.5922 0.7275 -0.0085 0.4282 -0.2418 0.2375 -0.3489 0.1236 -0.3779 0.0560 -0.3807 0.0172 -0.3692 -0.0028 -0.3503 -0.0102 -0.3273 -0.0088 -0.3023 -0.0014 -0.2765 0.0103 -0.2509 0.0248 -0.2261 0.0412 -0.2026 0.0586 -0.1805 0.0764 -0.1603 0.0941 -0.1420 0.1114 -0.1256 0.1281 -0.1112 0.1438 -0.0988 0.1586 -0.0884 0.1722 -0.0799 0.1847 -0.0733 0.1961 -0.0685 0.2064 -0.0656 0.2156 -0.0645 0.2239 -0.0651 0.2313 -0.0674 0.2379 -0.0714 0.2440 -0.0768 0.2495 -0.0835 0.2548 -0.0913 0.2599 -0.0999 0.2650 -0.1091 0.2704 -0.1185 0.2762 -0.1277 0.2827 -0.1365 0.2900 -0.1444 0.2985 -0.1514 0.3086 -0.1572 0.3206 -0.1617 0.3350 -0.1651 0.3525 -0.1675 0.3750 -0.1690 0.4041 -0.1698 0.4380 -0.1703 0.5699 -0.1705 -0.8121 -0.1706 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 2.500 0.052 0.127 -0.033 1.000 1.000 0.0000 -0.4816 Cpi Cpv ----------------- -0.8087 -0.1847 -0.6439 -0.1847 0.4154 -0.1847 0.3908 -0.1847 0.3624 -0.1847 0.3382 -0.1847 0.3144 -0.1847 0.2911 -0.1847 0.2683 -0.1848 0.2453 -0.1848 0.2221 -0.1849 0.1983 -0.1850 0.1736 -0.1852 0.1479 -0.1853 0.1211 -0.1855 0.0927 -0.1858 0.0628 -0.1861 0.0312 -0.1864 -0.0023 -0.1868 -0.0377 -0.1872 -0.0751 -0.1877 -0.1144 -0.1883 -0.1559 -0.1891 -0.1992 -0.1900 -0.2444 -0.1911 -0.2913 -0.1926 -0.3398 -0.1945 -0.3895 -0.1971 -0.4401 -0.2006 -0.4913 -0.2055 -0.5426 -0.2124 -0.5936 -0.2222 -0.6436 -0.2362 -0.6922 -0.2558 -0.7388 -0.2815 -0.7827 -0.3143 -0.8233 -0.3526 -0.8601 -0.3920 -0.8926 -0.4275 -0.9202 -0.4556 -0.9425 -0.4741 -0.9595 -0.4816 -0.9707 -0.4770 -0.9763 -0.4591 -0.9760 -0.4262 -0.9698 -0.3753 -0.9568 -0.3015 -0.9338 -0.1971 -0.8912 -0.0377 -0.7951 0.1921 -0.5455 0.5695 0.2107 0.9793 0.9832 0.6890 0.8129 0.1137 0.5239 -0.1413 0.3243 -0.2656 0.1991 -0.3098 0.1211 -0.3244 0.0736 -0.3221 0.0463 -0.3103 0.0328 -0.2931 0.0290 -0.2729 0.0321 -0.2510 0.0400 -0.2287 0.0514 -0.2067 0.0649 -0.1854 0.0798 -0.1654 0.0955 -0.1468 0.1114 -0.1299 0.1270 -0.1149 0.1422 -0.1017 0.1567 -0.0903 0.1703 -0.0809 0.1829 -0.0734 0.1944 -0.0678 0.2050 -0.0640 0.2145 -0.0621 0.2230 -0.0620 0.2306 -0.0637 0.2375 -0.0671 0.2436 -0.0721 0.2492 -0.0786 0.2543 -0.0865 0.2591 -0.0954 0.2639 -0.1053 0.2687 -0.1156 0.2737 -0.1261 0.2792 -0.1365 0.2854 -0.1463 0.2925 -0.1552 0.3008 -0.1630 0.3106 -0.1695 0.3224 -0.1747 0.3367 -0.1785 0.3540 -0.1812 0.3763 -0.1829 0.4054 -0.1838 0.4391 -0.1843 0.5707 -0.1845 -0.8087 -0.1847 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 3.000 0.054 0.161 -0.034 1.000 1.000 0.0000 -0.5035 Cpi Cpv ----------------- -0.8051 -0.1988 -0.6407 -0.1988 0.4165 -0.1988 0.3919 -0.1988 0.3635 -0.1988 0.3393 -0.1989 0.3154 -0.1989 0.2921 -0.1989 0.2691 -0.1989 0.2460 -0.1990 0.2226 -0.1991 0.1986 -0.1992 0.1737 -0.1993 0.1477 -0.1995 0.1205 -0.1997 0.0918 -0.1999 0.0615 -0.2001 0.0294 -0.2004 -0.0046 -0.2007 -0.0406 -0.2011 -0.0786 -0.2016 -0.1187 -0.2021 -0.1609 -0.2028 -0.2052 -0.2035 -0.2514 -0.2045 -0.2995 -0.2057 -0.3492 -0.2073 -0.4003 -0.2095 -0.4524 -0.2125 -0.5054 -0.2166 -0.5586 -0.2224 -0.6116 -0.2307 -0.6640 -0.2428 -0.7152 -0.2599 -0.7645 -0.2835 -0.8115 -0.3141 -0.8556 -0.3517 -0.8961 -0.3928 -0.9328 -0.4320 -0.9650 -0.4650 -0.9927 -0.4889 -1.0156 -0.5021 -1.0338 -0.5035 -1.0475 -0.4920 -1.0570 -0.4659 -1.0629 -0.4226 -1.0652 -0.3576 -1.0626 -0.2625 -1.0480 -0.1162 -0.9909 0.1055 -0.7908 0.4807 -0.0276 0.9487 0.9368 0.7718 0.8823 0.2266 0.6108 -0.0463 0.4060 -0.1858 0.2712 -0.2442 0.1841 -0.2699 0.1285 -0.2761 0.0943 -0.2713 0.0750 -0.2596 0.0663 -0.2440 0.0652 -0.2260 0.0695 -0.2069 0.0776 -0.1876 0.0885 -0.1686 0.1010 -0.1505 0.1146 -0.1337 0.1286 -0.1183 0.1426 -0.1045 0.1564 -0.0925 0.1695 -0.0823 0.1820 -0.0739 0.1935 -0.0674 0.2042 -0.0628 0.2139 -0.0600 0.2227 -0.0590 0.2305 -0.0600 0.2375 -0.0627 0.2438 -0.0671 0.2494 -0.0732 0.2545 -0.0808 0.2591 -0.0898 0.2636 -0.0998 0.2679 -0.1108 0.2724 -0.1223 0.2771 -0.1339 0.2823 -0.1454 0.2883 -0.1562 0.2951 -0.1661 0.3031 -0.1748 0.3128 -0.1820 0.3244 -0.1877 0.3385 -0.1920 0.3556 -0.1949 0.3778 -0.1968 0.4067 -0.1979 0.4403 -0.1985 0.5716 -0.1987 -0.8051 -0.1988 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 3.500 0.056 0.194 -0.035 1.000 1.000 0.0000 -0.5280 Cpi Cpv ----------------- -0.8012 -0.2130 -0.6371 -0.2130 0.4178 -0.2130 0.3931 -0.2130 0.3648 -0.2130 0.3404 -0.2130 0.3165 -0.2131 0.2931 -0.2131 0.2700 -0.2131 0.2468 -0.2132 0.2232 -0.2133 0.1990 -0.2134 0.1738 -0.2135 0.1476 -0.2136 0.1201 -0.2138 0.0910 -0.2140 0.0603 -0.2142 0.0278 -0.2145 -0.0067 -0.2148 -0.0433 -0.2151 -0.0820 -0.2155 -0.1228 -0.2160 -0.1659 -0.2165 -0.2110 -0.2172 -0.2583 -0.2180 -0.3075 -0.2190 -0.3584 -0.2204 -0.4109 -0.2222 -0.4646 -0.2247 -0.5193 -0.2281 -0.5744 -0.2330 -0.6295 -0.2400 -0.6843 -0.2502 -0.7380 -0.2650 -0.7902 -0.2861 -0.8403 -0.3142 -0.8878 -0.3501 -0.9322 -0.3918 -0.9731 -0.4341 -1.0101 -0.4717 -1.0432 -0.5012 -1.0723 -0.5203 -1.0976 -0.5280 -1.1196 -0.5230 -1.1393 -0.5040 -1.1577 -0.4687 -1.1762 -0.4126 -1.1952 -0.3278 -1.2107 -0.1951 -1.1966 0.0166 -1.0539 0.3858 -0.2971 0.9054 0.8608 0.8408 0.9357 0.3302 0.6891 0.0431 0.4825 -0.1094 0.3401 -0.1812 0.2448 -0.2172 0.1818 -0.2316 0.1412 -0.2332 0.1165 -0.2270 0.1030 -0.2158 0.0978 -0.2015 0.0986 -0.1855 0.1037 -0.1688 0.1119 -0.1522 0.1221 -0.1360 0.1336 -0.1209 0.1458 -0.1070 0.1582 -0.0946 0.1705 -0.0838 0.1824 -0.0747 0.1937 -0.0674 0.2043 -0.0619 0.2140 -0.0582 0.2229 -0.0564 0.2309 -0.0564 0.2381 -0.0583 0.2445 -0.0620 0.2502 -0.0674 0.2553 -0.0746 0.2599 -0.0832 0.2641 -0.0932 0.2682 -0.1044 0.2721 -0.1165 0.2763 -0.1291 0.2806 -0.1418 0.2855 -0.1543 0.2912 -0.1662 0.2978 -0.1770 0.3056 -0.1865 0.3150 -0.1944 0.3264 -0.2007 0.3404 -0.2054 0.3573 -0.2087 0.3793 -0.2108 0.4081 -0.2120 0.4416 -0.2126 0.5726 -0.2129 -0.8012 -0.2130 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 4.000 0.059 0.225 -0.035 1.000 1.000 0.0000 -0.5519 Cpi Cpv ----------------- -0.7970 -0.2272 -0.6334 -0.2272 0.4191 -0.2272 0.3945 -0.2272 0.3661 -0.2272 0.3417 -0.2272 0.3178 -0.2272 0.2943 -0.2273 0.2711 -0.2273 0.2477 -0.2273 0.2240 -0.2274 0.1995 -0.2275 0.1742 -0.2276 0.1477 -0.2277 0.1198 -0.2279 0.0904 -0.2281 0.0593 -0.2283 0.0263 -0.2285 -0.0087 -0.2288 -0.0459 -0.2291 -0.0852 -0.2295 -0.1268 -0.2299 -0.1706 -0.2303 -0.2167 -0.2309 -0.2649 -0.2316 -0.3153 -0.2324 -0.3675 -0.2336 -0.4214 -0.2351 -0.4767 -0.2371 -0.5330 -0.2400 -0.5901 -0.2440 -0.6473 -0.2499 -0.7044 -0.2585 -0.7607 -0.2711 -0.8157 -0.2894 -0.8690 -0.3149 -0.9200 -0.3482 -0.9683 -0.3893 -1.0135 -0.4338 -1.0554 -0.4758 -1.0940 -0.5107 -1.1294 -0.5360 -1.1620 -0.5500 -1.1927 -0.5519 -1.2229 -0.5403 -1.2544 -0.5131 -1.2898 -0.4665 -1.3316 -0.3924 -1.3793 -0.2740 -1.4120 -0.0741 -1.3347 0.2855 -0.5977 0.8506 0.7553 0.8965 0.9731 0.4247 0.7586 0.1270 0.5538 -0.0367 0.4056 -0.1209 0.3033 -0.1664 0.2336 -0.1884 0.1870 -0.1963 0.1571 -0.1952 0.1391 -0.1883 0.1300 -0.1776 0.1274 -0.1647 0.1295 -0.1506 0.1351 -0.1361 0.1430 -0.1219 0.1525 -0.1085 0.1629 -0.0961 0.1738 -0.0850 0.1847 -0.0754 0.1953 -0.0674 0.2055 -0.0612 0.2150 -0.0567 0.2239 -0.0540 0.2319 -0.0531 0.2392 -0.0541 0.2457 -0.0570 0.2515 -0.0616 0.2566 -0.0681 0.2612 -0.0762 0.2654 -0.0858 0.2692 -0.0969 0.2728 -0.1091 0.2764 -0.1223 0.2802 -0.1359 0.2843 -0.1497 0.2889 -0.1633 0.2943 -0.1762 0.3006 -0.1879 0.3081 -0.1982 0.3174 -0.2069 0.3286 -0.2137 0.3423 -0.2189 0.3591 -0.2224 0.3810 -0.2247 0.4096 -0.2261 0.4429 -0.2267 0.5736 -0.2270 -0.7970 -0.2272 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 4.500 0.062 0.256 -0.036 1.000 1.000 0.0000 -0.5784 Cpi Cpv ----------------- -0.7926 -0.2413 -0.6294 -0.2413 0.4205 -0.2413 0.3959 -0.2413 0.3675 -0.2413 0.3431 -0.2413 0.3191 -0.2414 0.2955 -0.2414 0.2722 -0.2414 0.2487 -0.2415 0.2248 -0.2415 0.2002 -0.2416 0.1746 -0.2417 0.1478 -0.2418 0.1197 -0.2420 0.0899 -0.2421 0.0584 -0.2423 0.0249 -0.2426 -0.0106 -0.2428 -0.0483 -0.2431 -0.0882 -0.2434 -0.1305 -0.2437 -0.1752 -0.2442 -0.2222 -0.2446 -0.2714 -0.2452 -0.3229 -0.2459 -0.3764 -0.2469 -0.4317 -0.2481 -0.4885 -0.2498 -0.5466 -0.2521 -0.6055 -0.2555 -0.6649 -0.2604 -0.7243 -0.2675 -0.7833 -0.2781 -0.8412 -0.2937 -0.8976 -0.3163 -0.9522 -0.3468 -1.0044 -0.3859 -1.0540 -0.4313 -1.1009 -0.4769 -1.1451 -0.5172 -1.1869 -0.5487 -1.2271 -0.5695 -1.2667 -0.5784 -1.3077 -0.5744 -1.3528 -0.5557 -1.4059 -0.5188 -1.4717 -0.4561 -1.5537 -0.3523 -1.6371 -0.1660 -1.6330 0.1808 -0.9294 0.7852 0.6202 0.9394 0.9944 0.5102 0.8194 0.2053 0.6199 0.0326 0.4678 -0.0633 0.3595 -0.1175 0.2838 -0.1467 0.2317 -0.1605 0.1968 -0.1643 0.1746 -0.1615 0.1617 -0.1542 0.1558 -0.1443 0.1551 -0.1327 0.1581 -0.1205 0.1638 -0.1082 0.1713 -0.0964 0.1800 -0.0855 0.1893 -0.0758 0.1988 -0.0674 0.2082 -0.0605 0.2173 -0.0553 0.2259 -0.0518 0.2338 -0.0501 0.2411 -0.0502 0.2476 -0.0521 0.2535 -0.0559 0.2586 -0.0615 0.2632 -0.0689 0.2673 -0.0780 0.2709 -0.0887 0.2743 -0.1007 0.2776 -0.1140 0.2808 -0.1282 0.2842 -0.1429 0.2880 -0.1577 0.2923 -0.1723 0.2974 -0.1861 0.3035 -0.1988 0.3108 -0.2099 0.3198 -0.2192 0.3308 -0.2267 0.3444 -0.2322 0.3610 -0.2361 0.3827 -0.2386 0.4112 -0.2401 0.4444 -0.2408 0.5747 -0.2412 -0.7926 -0.2413 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 5.000 0.065 0.285 -0.037 1.000 1.000 0.0000 -0.6060 Cpi Cpv ----------------- -0.7879 -0.2553 -0.6251 -0.2553 0.4220 -0.2553 0.3974 -0.2553 0.3690 -0.2553 0.3446 -0.2554 0.3205 -0.2554 0.2969 -0.2554 0.2735 -0.2554 0.2499 -0.2555 0.2258 -0.2555 0.2010 -0.2556 0.1751 -0.2557 0.1481 -0.2558 0.1197 -0.2560 0.0895 -0.2561 0.0576 -0.2563 0.0237 -0.2565 -0.0123 -0.2567 -0.0506 -0.2570 -0.0911 -0.2573 -0.1342 -0.2576 -0.1796 -0.2579 -0.2275 -0.2583 -0.2778 -0.2588 -0.3303 -0.2594 -0.3851 -0.2602 -0.4418 -0.2612 -0.5002 -0.2626 -0.5600 -0.2645 -0.6209 -0.2673 -0.6824 -0.2713 -0.7442 -0.2772 -0.8057 -0.2859 -0.8665 -0.2991 -0.9262 -0.3185 -0.9843 -0.3461 -1.0406 -0.3823 -1.0947 -0.4270 -1.1466 -0.4753 -1.1965 -0.5205 -1.2449 -0.5583 -1.2927 -0.5859 -1.3415 -0.6021 -1.3938 -0.6060 -1.4530 -0.5960 -1.5245 -0.5691 -1.6155 -0.5183 -1.7339 -0.4297 -1.8719 -0.2583 -1.9489 0.0724 -1.2920 0.7105 0.4556 0.9703 0.9998 0.5872 0.8714 0.2783 0.6807 0.0983 0.5267 -0.0085 0.4134 -0.0705 0.3324 -0.1065 0.2752 -0.1259 0.2358 -0.1343 0.2094 -0.1354 0.1930 -0.1315 0.1840 -0.1244 0.1804 -0.1154 0.1810 -0.1053 0.1845 -0.0949 0.1901 -0.0847 0.1971 -0.0753 0.2048 -0.0669 0.2130 -0.0597 0.2212 -0.0539 0.2292 -0.0498 0.2367 -0.0473 0.2438 -0.0465 0.2502 -0.0476 0.2561 -0.0504 0.2612 -0.0551 0.2658 -0.0617 0.2699 -0.0700 0.2734 -0.0800 0.2766 -0.0916 0.2796 -0.1047 0.2824 -0.1189 0.2853 -0.1341 0.2884 -0.1498 0.2918 -0.1657 0.2958 -0.1813 0.3007 -0.1961 0.3065 -0.2096 0.3136 -0.2215 0.3224 -0.2315 0.3332 -0.2395 0.3465 -0.2455 0.3630 -0.2497 0.3846 -0.2524 0.4128 -0.2540 0.4459 -0.2548 0.5758 -0.2552 -0.7879 -0.2553 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 5.500 0.069 0.312 -0.038 1.000 1.000 0.0000 -0.6347 Cpi Cpv ----------------- -0.7829 -0.2693 -0.6206 -0.2693 0.4235 -0.2693 0.3990 -0.2693 0.3706 -0.2693 0.3462 -0.2693 0.3221 -0.2693 0.2984 -0.2693 0.2749 -0.2693 0.2511 -0.2694 0.2269 -0.2694 0.2019 -0.2695 0.1758 -0.2696 0.1485 -0.2697 0.1198 -0.2698 0.0893 -0.2700 0.0570 -0.2702 0.0227 -0.2703 -0.0138 -0.2706 -0.0527 -0.2708 -0.0939 -0.2710 -0.1376 -0.2713 -0.1839 -0.2716 -0.2326 -0.2720 -0.2839 -0.2724 -0.3376 -0.2729 -0.3936 -0.2735 -0.4517 -0.2744 -0.5116 -0.2755 -0.5732 -0.2771 -0.6360 -0.2793 -0.6997 -0.2826 -0.7638 -0.2874 -0.8280 -0.2946 -0.8918 -0.3055 -0.9547 -0.3219 -1.0165 -0.3460 -1.0767 -0.3790 -1.1354 -0.4216 -1.1924 -0.4710 -1.2481 -0.5205 -1.3033 -0.5643 -1.3590 -0.5989 -1.4172 -0.6227 -1.4810 -0.6347 -1.5548 -0.6338 -1.6456 -0.6171 -1.7630 -0.5787 -1.9198 -0.5055 -2.1162 -0.3504 -2.2822 -0.0385 -1.6855 0.6277 0.2616 0.9899 0.9891 0.6560 0.9146 0.3457 0.7363 0.1606 0.5821 0.0435 0.4651 -0.0255 0.3794 -0.0678 0.3176 -0.0925 0.2738 -0.1053 0.2437 -0.1102 0.2238 -0.1095 0.2117 -0.1052 0.2055 -0.0985 0.2037 -0.0905 0.2051 -0.0820 0.2088 -0.0734 0.2140 -0.0655 0.2203 -0.0583 0.2271 -0.0523 0.2341 -0.0477 0.2410 -0.0446 0.2476 -0.0430 0.2538 -0.0432 0.2595 -0.0452 0.2646 -0.0490 0.2691 -0.0546 0.2731 -0.0620 0.2766 -0.0713 0.2796 -0.0822 0.2824 -0.0948 0.2849 -0.1088 0.2873 -0.1240 0.2898 -0.1401 0.2926 -0.1568 0.2957 -0.1737 0.2994 -0.1902 0.3040 -0.2059 0.3096 -0.2204 0.3164 -0.2331 0.3250 -0.2437 0.3356 -0.2523 0.3488 -0.2587 0.3651 -0.2632 0.3865 -0.2661 0.4146 -0.2678 0.4475 -0.2687 0.5770 -0.2691 -0.7829 -0.2693 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 6.000 0.072 0.339 -0.040 1.000 1.000 0.0000 -0.6686 Cpi Cpv ----------------- -0.7777 -0.2831 -0.6159 -0.2831 0.4252 -0.2831 0.4007 -0.2831 0.3723 -0.2831 0.3479 -0.2831 0.3237 -0.2831 0.2999 -0.2831 0.2764 -0.2831 0.2525 -0.2832 0.2281 -0.2832 0.2029 -0.2833 0.1766 -0.2834 0.1491 -0.2835 0.1200 -0.2836 0.0892 -0.2838 0.0566 -0.2839 0.0218 -0.2841 -0.0152 -0.2843 -0.0546 -0.2845 -0.0965 -0.2847 -0.1409 -0.2850 -0.1879 -0.2853 -0.2376 -0.2856 -0.2899 -0.2859 -0.3447 -0.2864 -0.4019 -0.2869 -0.4614 -0.2876 -0.5229 -0.2885 -0.5862 -0.2897 -0.6510 -0.2915 -0.7168 -0.2942 -0.7833 -0.2981 -0.8502 -0.3040 -0.9169 -0.3130 -0.9831 -0.3266 -1.0485 -0.3471 -1.1129 -0.3767 -1.1761 -0.4159 -1.2384 -0.4647 -1.3000 -0.5172 -1.3621 -0.5666 -1.4259 -0.6083 -1.4938 -0.6399 -1.5695 -0.6603 -1.6584 -0.6686 -1.7691 -0.6625 -1.9141 -0.6368 -2.1113 -0.5795 -2.3699 -0.4418 -2.6328 -0.1511 -2.1096 0.5380 0.0382 0.9990 0.9623 0.7176 0.9490 0.4073 0.7866 0.2200 0.6342 0.0925 0.5145 0.0177 0.4247 -0.0306 0.3587 -0.0602 0.3110 -0.0773 0.2772 -0.0857 0.2541 -0.0882 0.2391 -0.0865 0.2303 -0.0821 0.2261 -0.0762 0.2255 -0.0694 0.2273 -0.0625 0.2310 -0.0559 0.2358 -0.0501 0.2413 -0.0453 0.2471 -0.0418 0.2529 -0.0396 0.2586 -0.0391 0.2639 -0.0402 0.2688 -0.0431 0.2732 -0.0478 0.2771 -0.0543 0.2804 -0.0626 0.2834 -0.0727 0.2859 -0.0846 0.2882 -0.0981 0.2903 -0.1130 0.2924 -0.1291 0.2945 -0.1462 0.2969 -0.1639 0.2997 -0.1817 0.3031 -0.1992 0.3074 -0.2158 0.3128 -0.2310 0.3194 -0.2445 0.3277 -0.2559 0.3381 -0.2649 0.3512 -0.2718 0.3673 -0.2766 0.3885 -0.2797 0.4165 -0.2815 0.4492 -0.2824 0.5783 -0.2828 -0.7777 -0.2831 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 6.500 0.076 0.364 -0.041 1.000 1.000 0.0000 -0.7047 Cpi Cpv ----------------- -0.7722 -0.2968 -0.6109 -0.2968 0.4269 -0.2968 0.4024 -0.2968 0.3741 -0.2968 0.3497 -0.2968 0.3255 -0.2968 0.3016 -0.2969 0.2780 -0.2969 0.2539 -0.2969 0.2294 -0.2970 0.2040 -0.2970 0.1775 -0.2971 0.1498 -0.2972 0.1204 -0.2974 0.0893 -0.2975 0.0562 -0.2976 0.0210 -0.2978 -0.0165 -0.2980 -0.0564 -0.2982 -0.0989 -0.2984 -0.1440 -0.2986 -0.1918 -0.2989 -0.2424 -0.2992 -0.2956 -0.2995 -0.3516 -0.2998 -0.4101 -0.3003 -0.4709 -0.3008 -0.5340 -0.3016 -0.5991 -0.3026 -0.6658 -0.3040 -0.7337 -0.3062 -0.8027 -0.3093 -0.8722 -0.3141 -0.9419 -0.3214 -1.0114 -0.3325 -1.0805 -0.3496 -1.1490 -0.3752 -1.2169 -0.4107 -1.2845 -0.4570 -1.3522 -0.5108 -1.4212 -0.5651 -1.4933 -0.6136 -1.5711 -0.6531 -1.6590 -0.6822 -1.7636 -0.6999 -1.8949 -0.7047 -2.0687 -0.6923 -2.3084 -0.6566 -2.6331 -0.5182 -3.0006 -0.2850 -2.5644 0.4634 -0.2145 0.9985 0.9196 0.7787 0.9746 0.4577 0.8316 0.2792 0.6828 0.1369 0.5615 0.0591 0.4684 0.0051 0.3987 -0.0293 0.3474 -0.0503 0.3102 -0.0621 0.2839 -0.0675 0.2661 -0.0684 0.2548 -0.0663 0.2484 -0.0623 0.2457 -0.0573 0.2458 -0.0520 0.2478 -0.0468 0.2512 -0.0423 0.2554 -0.0386 0.2600 -0.0361 0.2648 -0.0350 0.2695 -0.0355 0.2740 -0.0375 0.2781 -0.0413 0.2818 -0.0469 0.2851 -0.0542 0.2878 -0.0634 0.2903 -0.0744 0.2923 -0.0872 0.2942 -0.1015 0.2958 -0.1174 0.2975 -0.1344 0.2993 -0.1524 0.3013 -0.1710 0.3038 -0.1898 0.3070 -0.2082 0.3110 -0.2256 0.3161 -0.2417 0.3224 -0.2559 0.3306 -0.2679 0.3408 -0.2775 0.3536 -0.2848 0.3695 -0.2899 0.3906 -0.2932 0.4184 -0.2951 0.4510 -0.2961 0.5796 -0.2966 -0.7722 -0.2968 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 7.000 0.080 0.387 -0.042 1.000 1.000 0.0000 -0.7449 Cpi Cpv ----------------- -0.7664 -0.3105 -0.6057 -0.3105 0.4287 -0.3105 0.4043 -0.3105 0.3760 -0.3105 0.3516 -0.3105 0.3273 -0.3105 0.3034 -0.3106 0.2797 -0.3106 0.2555 -0.3106 0.2309 -0.3107 0.2053 -0.3107 0.1786 -0.3108 0.1506 -0.3109 0.1210 -0.3110 0.0895 -0.3112 0.0561 -0.3113 0.0204 -0.3115 -0.0175 -0.3117 -0.0580 -0.3118 -0.1011 -0.3121 -0.1469 -0.3123 -0.1955 -0.3125 -0.2470 -0.3128 -0.3012 -0.3130 -0.3583 -0.3133 -0.4180 -0.3137 -0.4803 -0.3142 -0.5449 -0.3148 -0.6117 -0.3156 -0.6804 -0.3168 -0.7505 -0.3185 -0.8219 -0.3210 -0.8941 -0.3249 -0.9668 -0.3307 -1.0396 -0.3398 -1.1125 -0.3538 -1.1852 -0.3753 -1.2578 -0.4069 -1.3307 -0.4493 -1.4046 -0.5023 -1.4808 -0.5600 -1.5613 -0.6149 -1.6492 -0.6624 -1.7498 -0.7003 -1.8704 -0.7279 -2.0232 -0.7438 -2.2269 -0.7449 -2.5111 -0.7254 -2.9056 -0.6043 -3.3854 -0.4001 -3.0496 0.3657 -0.4965 0.9887 0.8608 0.8225 0.9914 0.5127 0.8713 0.3296 0.7281 0.1818 0.6062 0.0986 0.5105 0.0394 0.4375 0.0007 0.3828 -0.0241 0.3424 -0.0392 0.3132 -0.0474 0.2928 -0.0508 0.2790 -0.0509 0.2704 -0.0489 0.2658 -0.0456 0.2641 -0.0418 0.2646 -0.0380 0.2666 -0.0347 0.2695 -0.0322 0.2730 -0.0308 0.2768 -0.0307 0.2805 -0.0321 0.2842 -0.0350 0.2875 -0.0397 0.2905 -0.0461 0.2931 -0.0544 0.2953 -0.0644 0.2972 -0.0763 0.2988 -0.0899 0.3002 -0.1051 0.3014 -0.1218 0.3027 -0.1398 0.3041 -0.1587 0.3058 -0.1782 0.3080 -0.1979 0.3109 -0.2171 0.3146 -0.2355 0.3194 -0.2524 0.3256 -0.2673 0.3335 -0.2800 0.3435 -0.2901 0.3562 -0.2978 0.3719 -0.3032 0.3928 -0.3067 0.4204 -0.3087 0.4528 -0.3098 0.5810 -0.3103 -0.7664 -0.3105 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 7.500 0.084 0.410 -0.044 1.000 1.000 0.0000 -0.7938 Cpi Cpv ----------------- -0.7604 -0.3242 -0.6003 -0.3242 0.4307 -0.3242 0.4062 -0.3242 0.3780 -0.3242 0.3535 -0.3242 0.3293 -0.3243 0.3053 -0.3243 0.2815 -0.3243 0.2572 -0.3243 0.2324 -0.3244 0.2067 -0.3245 0.1798 -0.3245 0.1515 -0.3246 0.1216 -0.3247 0.0898 -0.3249 0.0560 -0.3250 0.0200 -0.3252 -0.0185 -0.3254 -0.0595 -0.3255 -0.1032 -0.3257 -0.1497 -0.3259 -0.1991 -0.3262 -0.2514 -0.3264 -0.3066 -0.3267 -0.3648 -0.3269 -0.4258 -0.3273 -0.4894 -0.3277 -0.5556 -0.3282 -0.6242 -0.3288 -0.6947 -0.3298 -0.7671 -0.3311 -0.8409 -0.3331 -0.9158 -0.3362 -0.9915 -0.3409 -1.0677 -0.3483 -1.1443 -0.3596 -1.2212 -0.3773 -1.2987 -0.4043 -1.3770 -0.4425 -1.4572 -0.4927 -1.5406 -0.5518 -1.6297 -0.6120 -1.7281 -0.6672 -1.8416 -0.7142 -1.9788 -0.7518 -2.1537 -0.7791 -2.3886 -0.7938 -2.7192 -0.7901 -3.1873 -0.6900 -3.7873 -0.5121 -3.5650 0.2631 -0.8076 0.9705 0.7860 0.8603 0.9993 0.5633 0.9057 0.3767 0.7699 0.2245 0.6486 0.1364 0.5509 0.0723 0.4751 0.0295 0.4174 0.0012 0.3740 -0.0171 0.3421 -0.0280 0.3190 -0.0338 0.3029 -0.0360 0.2923 -0.0358 0.2858 -0.0342 0.2824 -0.0319 0.2813 -0.0295 0.2819 -0.0274 0.2836 -0.0260 0.2859 -0.0257 0.2887 -0.0266 0.2916 -0.0289 0.2944 -0.0328 0.2970 -0.0383 0.2993 -0.0456 0.3012 -0.0547 0.3029 -0.0656 0.3042 -0.0783 0.3053 -0.0928 0.3063 -0.1089 0.3071 -0.1265 0.3080 -0.1453 0.3090 -0.1651 0.3105 -0.1855 0.3123 -0.2060 0.3149 -0.2262 0.3184 -0.2454 0.3229 -0.2631 0.3288 -0.2788 0.3365 -0.2920 0.3463 -0.3027 0.3588 -0.3108 0.3744 -0.3165 0.3951 -0.3201 0.4225 -0.3223 0.4548 -0.3235 0.5824 -0.3240 -0.7604 -0.3242 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 8.000 0.089 0.432 -0.046 1.000 1.000 0.0000 -0.8507 Cpi Cpv ----------------- -0.7541 -0.3380 -0.5946 -0.3380 0.4326 -0.3380 0.4083 -0.3380 0.3801 -0.3380 0.3556 -0.3380 0.3313 -0.3380 0.3073 -0.3380 0.2834 -0.3381 0.2590 -0.3381 0.2341 -0.3382 0.2082 -0.3382 0.1811 -0.3383 0.1526 -0.3384 0.1224 -0.3385 0.0903 -0.3386 0.0561 -0.3388 0.0197 -0.3389 -0.0192 -0.3391 -0.0608 -0.3393 -0.1051 -0.3395 -0.1523 -0.3397 -0.2024 -0.3399 -0.2556 -0.3401 -0.3118 -0.3404 -0.3711 -0.3406 -0.4333 -0.3409 -0.4984 -0.3413 -0.5661 -0.3417 -0.6364 -0.3423 -0.7090 -0.3430 -0.7835 -0.3441 -0.8597 -0.3457 -0.9373 -0.3482 -1.0160 -0.3519 -1.0957 -0.3578 -1.1761 -0.3670 -1.2573 -0.3813 -1.3396 -0.4037 -1.4234 -0.4372 -1.5099 -0.4830 -1.6008 -0.5410 -1.6987 -0.6050 -1.8078 -0.6674 -1.9344 -0.7233 -2.0887 -0.7712 -2.2865 -0.8101 -2.5536 -0.8385 -2.9328 -0.8507 -3.4781 -0.7730 -4.2060 -0.6215 -4.1106 0.1577 -1.1477 0.9451 0.6953 0.8924 0.9984 0.6098 0.9348 0.4208 0.8082 0.2650 0.6886 0.1723 0.5897 0.1038 0.5115 0.0572 0.4510 0.0255 0.4049 0.0043 0.3703 -0.0092 0.3449 -0.0173 0.3266 -0.0216 0.3139 -0.0232 0.3055 -0.0232 0.3005 -0.0224 0.2979 -0.0213 0.2971 -0.0204 0.2976 -0.0202 0.2989 -0.0209 0.3007 -0.0228 0.3026 -0.0260 0.3046 -0.0308 0.3064 -0.0372 0.3081 -0.0454 0.3094 -0.0553 0.3105 -0.0670 0.3113 -0.0806 0.3119 -0.0959 0.3124 -0.1128 0.3128 -0.1313 0.3134 -0.1510 0.3141 -0.1716 0.3151 -0.1929 0.3167 -0.2143 0.3190 -0.2353 0.3222 -0.2554 0.3265 -0.2739 0.3322 -0.2903 0.3397 -0.3041 0.3493 -0.3153 0.3615 -0.3238 0.3769 -0.3298 0.3974 -0.3337 0.4247 -0.3360 0.4568 -0.3372 0.5839 -0.3377 -0.7541 -0.3380 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 8.500 0.093 0.452 -0.048 1.000 1.000 0.0000 -0.9068 Cpi Cpv ----------------- -0.7476 -0.3518 -0.5887 -0.3518 0.4347 -0.3518 0.4104 -0.3518 0.3822 -0.3518 0.3578 -0.3519 0.3335 -0.3519 0.3094 -0.3519 0.2854 -0.3519 0.2610 -0.3520 0.2359 -0.3520 0.2098 -0.3521 0.1825 -0.3522 0.1538 -0.3522 0.1233 -0.3524 0.0909 -0.3525 0.0564 -0.3526 0.0195 -0.3528 -0.0198 -0.3530 -0.0619 -0.3531 -0.1068 -0.3533 -0.1547 -0.3536 -0.2056 -0.3538 -0.2597 -0.3540 -0.3169 -0.3542 -0.3772 -0.3545 -0.4407 -0.3547 -0.5071 -0.3551 -0.5764 -0.3554 -0.6485 -0.3559 -0.7229 -0.3565 -0.7996 -0.3574 -0.8783 -0.3587 -0.9586 -0.3607 -1.0404 -0.3637 -1.1235 -0.3683 -1.2077 -0.3757 -1.2933 -0.3872 -1.3804 -0.4054 -1.4699 -0.4337 -1.5629 -0.4747 -1.6613 -0.5291 -1.7682 -0.5944 -1.8881 -0.6626 -2.0284 -0.7273 -2.2001 -0.7855 -2.4215 -0.8363 -2.7221 -0.8786 -3.1517 -0.9068 -3.7781 -0.8523 -4.6415 -0.7279 -4.6862 0.0508 -1.5169 0.9137 0.5886 0.9193 0.9887 0.6523 0.9585 0.4619 0.8431 0.3033 0.7262 0.2066 0.6267 0.1339 0.5466 0.0838 0.4837 0.0490 0.4351 0.0250 0.3981 0.0089 0.3703 -0.0014 0.3499 -0.0076 0.3353 -0.0110 0.3251 -0.0126 0.3185 -0.0132 0.3145 -0.0134 0.3124 -0.0138 0.3116 -0.0146 0.3118 -0.0164 0.3126 -0.0192 0.3137 -0.0234 0.3149 -0.0291 0.3160 -0.0363 0.3169 -0.0453 0.3177 -0.0561 0.3182 -0.0687 0.3185 -0.0831 0.3186 -0.0992 0.3187 -0.1169 0.3187 -0.1362 0.3188 -0.1568 0.3192 -0.1783 0.3199 -0.2005 0.3212 -0.2227 0.3232 -0.2446 0.3261 -0.2655 0.3302 -0.2847 0.3356 -0.3018 0.3429 -0.3163 0.3523 -0.3280 0.3643 -0.3369 0.3795 -0.3432 0.3999 -0.3473 0.4270 -0.3497 0.4588 -0.3510 0.5855 -0.3516 -0.7476 -0.3518 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 9.000 0.098 0.472 -0.050 1.000 1.000 0.0000 -0.9576 Cpi Cpv ----------------- -0.7408 -0.3658 -0.5826 -0.3658 0.4369 -0.3658 0.4126 -0.3658 0.3845 -0.3658 0.3600 -0.3659 0.3357 -0.3659 0.3116 -0.3659 0.2875 -0.3659 0.2630 -0.3660 0.2378 -0.3660 0.2116 -0.3661 0.1841 -0.3662 0.1551 -0.3662 0.1244 -0.3664 0.0917 -0.3665 0.0568 -0.3666 0.0195 -0.3668 -0.0203 -0.3670 -0.0629 -0.3672 -0.1084 -0.3674 -0.1569 -0.3676 -0.2086 -0.3678 -0.2635 -0.3680 -0.3217 -0.3683 -0.3832 -0.3685 -0.4478 -0.3688 -0.5157 -0.3691 -0.5865 -0.3694 -0.6603 -0.3698 -0.7367 -0.3704 -0.8156 -0.3711 -0.8967 -0.3722 -0.9798 -0.3737 -1.0647 -0.3761 -1.1512 -0.3798 -1.2393 -0.3857 -1.3292 -0.3949 -1.4213 -0.4095 -1.5165 -0.4326 -1.6160 -0.4680 -1.7221 -0.5174 -1.8381 -0.5811 -1.9691 -0.6532 -2.1233 -0.7258 -2.3130 -0.7942 -2.5587 -0.8570 -2.8938 -0.9132 -3.3758 -0.9576 -4.0870 -0.9270 -5.0935 -0.8301 -5.2916 -0.0562 -1.9148 0.8771 0.4660 0.9416 0.9701 0.6911 0.9769 0.5002 0.8745 0.3396 0.7615 0.2392 0.6621 0.1627 0.5805 0.1094 0.5155 0.0715 0.4646 0.0449 0.4253 0.0265 0.3954 0.0140 0.3729 0.0059 0.3564 0.0008 0.3446 -0.0024 0.3363 -0.0044 0.3309 -0.0059 0.3275 -0.0074 0.3256 -0.0094 0.3247 -0.0121 0.3246 -0.0159 0.3248 -0.0210 0.3251 -0.0276 0.3255 -0.0357 0.3258 -0.0455 0.3260 -0.0571 0.3259 -0.0705 0.3257 -0.0857 0.3254 -0.1027 0.3250 -0.1213 0.3246 -0.1414 0.3244 -0.1628 0.3244 -0.1852 0.3248 -0.2082 0.3257 -0.2313 0.3274 -0.2540 0.3301 -0.2757 0.3339 -0.2957 0.3391 -0.3136 0.3462 -0.3287 0.3554 -0.3409 0.3672 -0.3502 0.3823 -0.3568 0.4024 -0.3610 0.4293 -0.3636 0.4610 -0.3649 0.5872 -0.3655 -0.7408 -0.3658 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 9.500 0.103 0.490 -0.053 1.000 1.000 0.0000 -1.0026 Cpi Cpv ----------------- -0.7338 -0.3800 -0.5762 -0.3800 0.4391 -0.3800 0.4149 -0.3800 0.3868 -0.3800 0.3624 -0.3800 0.3381 -0.3801 0.3139 -0.3801 0.2898 -0.3801 0.2651 -0.3801 0.2398 -0.3802 0.2134 -0.3803 0.1857 -0.3803 0.1565 -0.3804 0.1256 -0.3806 0.0926 -0.3807 0.0573 -0.3808 0.0197 -0.3810 -0.0206 -0.3812 -0.0637 -0.3814 -0.1098 -0.3816 -0.1590 -0.3818 -0.2115 -0.3820 -0.2672 -0.3823 -0.3264 -0.3825 -0.3889 -0.3828 -0.4548 -0.3831 -0.5240 -0.3833 -0.5964 -0.3837 -0.6719 -0.3841 -0.7503 -0.3845 -0.8314 -0.3852 -0.9149 -0.3860 -1.0008 -0.3873 -1.0887 -0.3892 -1.1787 -0.3922 -1.2707 -0.3968 -1.3650 -0.4042 -1.4622 -0.4159 -1.5631 -0.4345 -1.6692 -0.4638 -1.7831 -0.5075 -1.9084 -0.5667 -2.0508 -0.6396 -2.2192 -0.7186 -2.4274 -0.7968 -2.6981 -0.8716 -3.0689 -0.9418 -3.6052 -1.0026 -4.4047 -0.9961 -5.5620 -0.9274 -5.9266 -0.1621 -2.3415 0.8364 0.3275 0.9595 0.9428 0.7263 0.9900 0.5358 0.9024 0.3738 0.7943 0.2701 0.6957 0.1903 0.6131 0.1339 0.5464 0.0933 0.4934 0.0641 0.4520 0.0434 0.4200 0.0289 0.3956 0.0190 0.3773 0.0122 0.3638 0.0075 0.3541 0.0041 0.3472 0.0014 0.3426 -0.0013 0.3395 -0.0043 0.3376 -0.0081 0.3365 -0.0129 0.3359 -0.0189 0.3355 -0.0263 0.3351 -0.0353 0.3348 -0.0460 0.3343 -0.0584 0.3337 -0.0726 0.3330 -0.0886 0.3322 -0.1064 0.3314 -0.1258 0.3306 -0.1468 0.3300 -0.1690 0.3296 -0.1922 0.3297 -0.2161 0.3304 -0.2401 0.3318 -0.2636 0.3342 -0.2861 0.3378 -0.3069 0.3428 -0.3255 0.3496 -0.3412 0.3586 -0.3539 0.3702 -0.3636 0.3851 -0.3705 0.4051 -0.3750 0.4317 -0.3776 0.4633 -0.3790 0.5888 -0.3797 -0.7338 -0.3800 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 10.000 0.109 0.508 -0.056 1.000 1.000 0.0000 -1.0587 Cpi Cpv ----------------- -0.7265 -0.3944 -0.5696 -0.3944 0.4414 -0.3944 0.4173 -0.3944 0.3893 -0.3944 0.3648 -0.3944 0.3405 -0.3944 0.3163 -0.3945 0.2921 -0.3945 0.2674 -0.3945 0.2419 -0.3946 0.2154 -0.3947 0.1875 -0.3947 0.1581 -0.3948 0.1269 -0.3950 0.0936 -0.3951 0.0580 -0.3952 0.0200 -0.3954 -0.0208 -0.3956 -0.0644 -0.3958 -0.1111 -0.3960 -0.1609 -0.3963 -0.2141 -0.3965 -0.2707 -0.3968 -0.3308 -0.3970 -0.3944 -0.3973 -0.4615 -0.3976 -0.5321 -0.3979 -0.6061 -0.3982 -0.6833 -0.3986 -0.7637 -0.3990 -0.8469 -0.3996 -0.9330 -0.4003 -1.0216 -0.4014 -1.1126 -0.4030 -1.2061 -0.4054 -1.3020 -0.4091 -1.4008 -0.4149 -1.5030 -0.4242 -1.6097 -0.4390 -1.7226 -0.4627 -1.8444 -0.4997 -1.9792 -0.5530 -2.1331 -0.6233 -2.3161 -0.7060 -2.5432 -0.7929 -2.8395 -0.8793 -3.2471 -0.9636 -3.8398 -1.0409 -4.7313 -1.0587 -6.0469 -1.0184 -6.5910 -0.2654 -2.7968 0.7928 0.1732 0.9735 0.9066 0.7582 0.9977 0.5687 0.9268 0.4061 0.8248 0.2994 0.7276 0.2166 0.6445 0.1574 0.5763 0.1142 0.5215 0.0826 0.4781 0.0597 0.4442 0.0433 0.4180 0.0315 0.3979 0.0231 0.3829 0.0170 0.3716 0.0123 0.3635 0.0083 0.3576 0.0045 0.3534 0.0004 0.3505 -0.0044 0.3485 -0.0101 0.3470 -0.0170 0.3458 -0.0253 0.3448 -0.0351 0.3438 -0.0466 0.3427 -0.0599 0.3416 -0.0749 0.3404 -0.0917 0.3391 -0.1103 0.3379 -0.1306 0.3367 -0.1523 0.3357 -0.1754 0.3350 -0.1995 0.3348 -0.2242 0.3351 -0.2491 0.3362 -0.2734 0.3384 -0.2968 0.3417 -0.3183 0.3465 -0.3375 0.3531 -0.3539 0.3619 -0.3672 0.3733 -0.3772 0.3880 -0.3844 0.4078 -0.3891 0.4343 -0.3919 0.4656 -0.3934 0.5906 -0.3941 -0.7265 -0.3944 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 10.500 0.114 0.525 -0.059 1.000 1.000 0.0000 -1.1139 Cpi Cpv ----------------- -0.7189 -0.4091 -0.5628 -0.4091 0.4438 -0.4091 0.4197 -0.4091 0.3918 -0.4091 0.3674 -0.4091 0.3430 -0.4091 0.3188 -0.4091 0.2946 -0.4091 0.2697 -0.4092 0.2442 -0.4092 0.2175 -0.4093 0.1894 -0.4094 0.1598 -0.4095 0.1284 -0.4096 0.0948 -0.4098 0.0589 -0.4099 0.0204 -0.4101 -0.0208 -0.4103 -0.0649 -0.4105 -0.1121 -0.4108 -0.1626 -0.4110 -0.2166 -0.4113 -0.2740 -0.4115 -0.3351 -0.4118 -0.3997 -0.4121 -0.4681 -0.4124 -0.5400 -0.4127 -0.6156 -0.4131 -0.6945 -0.4135 -0.7768 -0.4139 -0.8623 -0.4144 -0.9508 -0.4151 -1.0421 -0.4160 -1.1363 -0.4174 -1.2333 -0.4193 -1.3332 -0.4223 -1.4364 -0.4269 -1.5438 -0.4343 -1.6564 -0.4460 -1.7761 -0.4649 -1.9059 -0.4951 -2.0503 -0.5415 -2.2161 -0.6062 -2.4138 -0.6888 -2.6603 -0.7822 -2.9830 -0.8797 -3.4285 -0.9778 -4.0794 -1.0717 -5.0665 -1.1139 -6.5478 -1.1024 -7.2846 -0.3651 -3.2805 0.7470 0.0031 0.9841 0.8616 0.7871 1.0000 0.5993 0.9477 0.4366 0.8528 0.3272 0.7578 0.2417 0.6746 0.1800 0.6052 0.1343 0.5488 0.1004 0.5037 0.0755 0.4680 0.0572 0.4400 0.0437 0.4183 0.0338 0.4017 0.0262 0.3891 0.0202 0.3796 0.0150 0.3725 0.0101 0.3673 0.0049 0.3634 -0.0008 0.3604 -0.0075 0.3581 -0.0153 0.3561 -0.0244 0.3544 -0.0351 0.3528 -0.0475 0.3512 -0.0615 0.3495 -0.0774 0.3478 -0.0950 0.3461 -0.1144 0.3444 -0.1355 0.3428 -0.1581 0.3415 -0.1820 0.3404 -0.2070 0.3399 -0.2325 0.3399 -0.2582 0.3408 -0.2835 0.3427 -0.3076 0.3457 -0.3299 0.3503 -0.3499 0.3567 -0.3669 0.3652 -0.3806 0.3765 -0.3911 0.3910 -0.3986 0.4106 -0.4035 0.4369 -0.4064 0.4680 -0.4080 0.5924 -0.4087 -0.7189 -0.4091 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 11.000 0.120 0.542 -0.062 1.000 1.000 0.0000 -1.1785 Cpi Cpv ----------------- -0.7112 -0.4240 -0.5557 -0.4240 0.4463 -0.4240 0.4223 -0.4240 0.3944 -0.4240 0.3700 -0.4240 0.3457 -0.4240 0.3214 -0.4240 0.2971 -0.4240 0.2722 -0.4241 0.2465 -0.4241 0.2197 -0.4242 0.1915 -0.4243 0.1617 -0.4244 0.1300 -0.4245 0.0961 -0.4247 0.0598 -0.4249 0.0210 -0.4251 -0.0206 -0.4253 -0.0652 -0.4255 -0.1130 -0.4257 -0.1642 -0.4260 -0.2189 -0.4263 -0.2771 -0.4266 -0.3391 -0.4269 -0.4049 -0.4272 -0.4744 -0.4276 -0.5477 -0.4279 -0.6248 -0.4283 -0.7055 -0.4287 -0.7898 -0.4291 -0.8774 -0.4297 -0.9684 -0.4303 -1.0625 -0.4311 -1.1598 -0.4323 -1.2603 -0.4339 -1.3642 -0.4364 -1.4720 -0.4401 -1.5845 -0.4460 -1.7030 -0.4553 -1.8296 -0.4703 -1.9676 -0.4944 -2.1218 -0.5329 -2.2996 -0.5905 -2.5125 -0.6690 -2.7788 -0.7655 -3.1286 -0.8723 -3.6131 -0.9838 -4.3239 -1.0944 -5.4103 -1.1611 -7.0648 -1.1785 -8.0072 -0.4603 -3.7926 0.6998 -0.1827 0.9917 0.8079 0.8132 0.9970 0.6275 0.9651 0.4656 0.8784 0.3536 0.7863 0.2658 0.7034 0.2017 0.6332 0.1537 0.5754 0.1178 0.5287 0.0909 0.4913 0.0708 0.4617 0.0556 0.4384 0.0442 0.4203 0.0352 0.4063 0.0279 0.3956 0.0215 0.3874 0.0155 0.3811 0.0093 0.3762 0.0026 0.3723 -0.0050 0.3692 -0.0137 0.3665 -0.0237 0.3641 -0.0353 0.3618 -0.0484 0.3596 -0.0633 0.3574 -0.0800 0.3553 -0.0984 0.3531 -0.1187 0.3510 -0.1406 0.3490 -0.1640 0.3473 -0.1888 0.3459 -0.2146 0.3451 -0.2410 0.3448 -0.2675 0.3454 -0.2936 0.3470 -0.3186 0.3499 -0.3417 0.3542 -0.3624 0.3603 -0.3800 0.3687 -0.3943 0.3798 -0.4052 0.3940 -0.4130 0.4134 -0.4181 0.4395 -0.4212 0.4705 -0.4228 0.5943 -0.4236 -0.7112 -0.4240 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 11.500 0.127 0.558 -0.065 1.000 1.000 0.0000 -1.2457 Cpi Cpv ----------------- -0.7031 -0.4391 -0.5485 -0.4391 0.4489 -0.4391 0.4249 -0.4391 0.3971 -0.4391 0.3727 -0.4391 0.3484 -0.4391 0.3241 -0.4391 0.2998 -0.4391 0.2748 -0.4392 0.2490 -0.4392 0.2220 -0.4393 0.1936 -0.4394 0.1636 -0.4395 0.1317 -0.4397 0.0975 -0.4398 0.0610 -0.4400 0.0218 -0.4402 -0.0203 -0.4404 -0.0654 -0.4407 -0.1138 -0.4409 -0.1656 -0.4412 -0.2210 -0.4415 -0.2800 -0.4418 -0.3430 -0.4422 -0.4098 -0.4425 -0.4805 -0.4429 -0.5552 -0.4433 -0.6338 -0.4437 -0.7162 -0.4441 -0.8025 -0.4446 -0.8923 -0.4452 -0.9857 -0.4458 -1.0827 -0.4466 -1.1831 -0.4477 -1.2871 -0.4491 -1.3951 -0.4512 -1.5074 -0.4542 -1.6251 -0.4590 -1.7497 -0.4664 -1.8833 -0.4782 -2.0296 -0.4974 -2.1937 -0.5284 -2.3837 -0.5775 -2.6121 -0.6489 -2.8986 -0.7439 -3.2761 -0.8571 -3.8006 -0.9809 -4.5735 -1.1079 -5.7626 -1.1991 -7.5977 -1.2457 -8.7586 -0.5499 -4.3328 0.6520 -0.3842 0.9966 0.7453 0.8368 0.9886 0.6537 0.9790 0.4931 0.9016 0.3787 0.8130 0.2890 0.7309 0.2227 0.6602 0.1726 0.6013 0.1346 0.5531 0.1059 0.5142 0.0840 0.4830 0.0673 0.4583 0.0544 0.4388 0.0441 0.4235 0.0355 0.4115 0.0280 0.4021 0.0208 0.3948 0.0136 0.3889 0.0059 0.3842 -0.0026 0.3803 -0.0121 0.3769 -0.0230 0.3738 -0.0354 0.3709 -0.0494 0.3682 -0.0651 0.3654 -0.0826 0.3628 -0.1019 0.3602 -0.1229 0.3577 -0.1457 0.3553 -0.1700 0.3532 -0.1956 0.3515 -0.2223 0.3504 -0.2495 0.3498 -0.2770 0.3501 -0.3039 0.3515 -0.3297 0.3541 -0.3537 0.3581 -0.3750 0.3641 -0.3933 0.3722 -0.4082 0.3831 -0.4195 0.3972 -0.4276 0.4164 -0.4329 0.4423 -0.4361 0.4730 -0.4378 0.5962 -0.4387 -0.7031 -0.4391 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 12.000 0.133 0.574 -0.069 1.000 1.000 0.0000 -1.3035 Cpi Cpv ----------------- -0.6949 -0.4542 -0.5410 -0.4542 0.4515 -0.4542 0.4276 -0.4542 0.3999 -0.4542 0.3755 -0.4542 0.3512 -0.4543 0.3269 -0.4543 0.3025 -0.4543 0.2774 -0.4544 0.2516 -0.4544 0.2245 -0.4545 0.1959 -0.4546 0.1657 -0.4547 0.1335 -0.4548 0.0991 -0.4550 0.0622 -0.4552 0.0227 -0.4554 -0.0198 -0.4556 -0.0654 -0.4559 -0.1143 -0.4562 -0.1668 -0.4565 -0.2229 -0.4568 -0.2828 -0.4572 -0.3466 -0.4576 -0.4145 -0.4579 -0.4864 -0.4584 -0.5625 -0.4588 -0.6426 -0.4592 -0.7268 -0.4597 -0.8149 -0.4603 -0.9070 -0.4608 -1.0029 -0.4615 -1.1026 -0.4623 -1.2062 -0.4633 -1.3138 -0.4646 -1.4258 -0.4664 -1.5427 -0.4690 -1.6657 -0.4729 -1.7963 -0.4789 -1.9370 -0.4883 -2.0917 -0.5036 -2.2659 -0.5283 -2.4683 -0.5684 -2.7124 -0.6311 -3.0196 -0.7200 -3.4255 -0.8353 -3.9912 -0.9692 -4.8278 -1.1120 -6.1232 -1.2276 -8.1462 -1.3035 -9.5386 -0.6334 -4.9010 0.6043 -0.6013 0.9993 0.6740 0.8584 0.9749 0.6776 0.9894 0.5195 0.9223 0.4025 0.8379 0.3114 0.7571 0.2430 0.6862 0.1909 0.6264 0.1511 0.5770 0.1205 0.5366 0.0970 0.5040 0.0788 0.4779 0.0644 0.4570 0.0528 0.4404 0.0430 0.4273 0.0343 0.4168 0.0262 0.4084 0.0179 0.4017 0.0093 0.3961 -0.0001 0.3914 -0.0106 0.3873 -0.0223 0.3835 -0.0355 0.3801 -0.0504 0.3767 -0.0669 0.3735 -0.0852 0.3704 -0.1053 0.3673 -0.1272 0.3644 -0.1508 0.3617 -0.1759 0.3592 -0.2024 0.3572 -0.2299 0.3557 -0.2581 0.3549 -0.2864 0.3549 -0.3142 0.3560 -0.3409 0.3583 -0.3656 0.3622 -0.3877 0.3679 -0.4067 0.3759 -0.4221 0.3865 -0.4339 0.4004 -0.4423 0.4194 -0.4478 0.4451 -0.4512 0.4756 -0.4529 0.5982 -0.4538 -0.6949 -0.4542 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 12.500 0.141 0.590 -0.072 1.000 1.000 0.0000 -1.3362 Cpi Cpv ----------------- -0.6864 -0.4694 -0.5333 -0.4694 0.4542 -0.4694 0.4304 -0.4694 0.4027 -0.4694 0.3784 -0.4694 0.3541 -0.4694 0.3298 -0.4694 0.3054 -0.4695 0.2802 -0.4695 0.2542 -0.4696 0.2270 -0.4697 0.1983 -0.4698 0.1679 -0.4699 0.1355 -0.4700 0.1008 -0.4702 0.0636 -0.4704 0.0237 -0.4706 -0.0192 -0.4708 -0.0653 -0.4711 -0.1147 -0.4714 -0.1678 -0.4718 -0.2246 -0.4721 -0.2853 -0.4725 -0.3501 -0.4729 -0.4190 -0.4733 -0.4921 -0.4738 -0.5695 -0.4743 -0.6512 -0.4748 -0.7371 -0.4753 -0.8272 -0.4759 -0.9214 -0.4765 -1.0198 -0.4772 -1.1223 -0.4780 -1.2291 -0.4790 -1.3402 -0.4803 -1.4563 -0.4820 -1.5778 -0.4842 -1.7061 -0.4875 -1.8429 -0.4924 -1.9907 -0.5001 -2.1539 -0.5122 -2.3384 -0.5319 -2.5534 -0.5641 -2.8136 -0.6165 -3.1419 -0.6967 -3.5768 -0.8085 -4.1847 -0.9488 -5.0869 -1.1065 -6.4921 -1.2537 -8.7103 -1.3362 -10.3469 -0.7447 -5.4969 0.5852 -0.8340 1.0000 0.5940 0.8856 0.9558 0.6932 0.9963 0.5489 0.9406 0.4222 0.8611 0.3336 0.7820 0.2627 0.7113 0.2087 0.6507 0.1671 0.6002 0.1349 0.5586 0.1098 0.5247 0.0901 0.4972 0.0744 0.4750 0.0615 0.4572 0.0505 0.4429 0.0407 0.4314 0.0315 0.4220 0.0223 0.4144 0.0127 0.4080 0.0024 0.4025 -0.0090 0.3976 -0.0216 0.3933 -0.0356 0.3892 -0.0513 0.3853 -0.0686 0.3816 -0.0877 0.3780 -0.1087 0.3745 -0.1314 0.3712 -0.1558 0.3681 -0.1818 0.3653 -0.2091 0.3629 -0.2375 0.3611 -0.2665 0.3600 -0.2957 0.3598 -0.3244 0.3606 -0.3519 0.3627 -0.3775 0.3663 -0.4004 0.3718 -0.4200 0.3796 -0.4359 0.3901 -0.4482 0.4037 -0.4569 0.4226 -0.4627 0.4480 -0.4662 0.4783 -0.4680 0.6002 -0.4689 -0.6864 -0.4694 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 13.000 0.149 0.605 -0.076 1.000 1.000 0.0000 -1.3615 Cpi Cpv ----------------- -0.6776 -0.4843 -0.5254 -0.4843 0.4570 -0.4843 0.4333 -0.4843 0.4057 -0.4843 0.3814 -0.4843 0.3571 -0.4843 0.3328 -0.4844 0.3083 -0.4844 0.2831 -0.4844 0.2570 -0.4845 0.2297 -0.4846 0.2008 -0.4847 0.1702 -0.4848 0.1376 -0.4850 0.1026 -0.4851 0.0652 -0.4853 0.0249 -0.4856 -0.0184 -0.4858 -0.0649 -0.4861 -0.1149 -0.4864 -0.1686 -0.4868 -0.2261 -0.4872 -0.2876 -0.4876 -0.3533 -0.4880 -0.4233 -0.4885 -0.4976 -0.4890 -0.5763 -0.4895 -0.6595 -0.4900 -0.7471 -0.4906 -0.8392 -0.4913 -0.9356 -0.4920 -1.0365 -0.4927 -1.1418 -0.4936 -1.2517 -0.4946 -1.3665 -0.4959 -1.4866 -0.4974 -1.6128 -0.4995 -1.7465 -0.5024 -1.8894 -0.5066 -2.0445 -0.5129 -2.2163 -0.5227 -2.4111 -0.5384 -2.6390 -0.5643 -2.9155 -0.6070 -3.2654 -0.6766 -3.7299 -0.7806 -4.3810 -0.9223 -5.3508 -1.0926 -6.8692 -1.2670 -9.2897 -1.3615 -11.1832 -0.8285 -6.1206 0.5449 -1.0821 0.9987 0.5053 0.9014 0.9314 0.7153 0.9996 0.5719 0.9565 0.4446 0.8825 0.3547 0.8056 0.2821 0.7353 0.2264 0.6743 0.1831 0.6229 0.1493 0.5801 0.1226 0.5449 0.1015 0.5162 0.0844 0.4928 0.0703 0.4738 0.0581 0.4584 0.0472 0.4459 0.0370 0.4356 0.0268 0.4270 0.0163 0.4198 0.0050 0.4136 -0.0072 0.4080 -0.0206 0.4030 -0.0355 0.3984 -0.0519 0.3940 -0.0701 0.3897 -0.0900 0.3857 -0.1118 0.3817 -0.1353 0.3780 -0.1605 0.3746 -0.1873 0.3714 -0.2155 0.3687 -0.2448 0.3666 -0.2747 0.3652 -0.3048 0.3647 -0.3344 0.3653 -0.3627 0.3672 -0.3891 0.3705 -0.4127 0.3758 -0.4330 0.3834 -0.4496 0.3936 -0.4622 0.4071 -0.4713 0.4258 -0.4773 0.4510 -0.4809 0.4811 -0.4829 0.6023 -0.4838 -0.6776 -0.4843 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 13.500 0.157 0.620 -0.080 1.000 1.000 0.0000 -1.3867 Cpi Cpv ----------------- -0.6687 -0.4989 -0.5173 -0.4989 0.4599 -0.4989 0.4362 -0.4989 0.4087 -0.4989 0.3845 -0.4990 0.3602 -0.4990 0.3359 -0.4990 0.3113 -0.4990 0.2861 -0.4991 0.2599 -0.4991 0.2325 -0.4992 0.2035 -0.4993 0.1727 -0.4994 0.1398 -0.4996 0.1046 -0.4998 0.0668 -0.5000 0.0262 -0.5002 -0.0175 -0.5005 -0.0645 -0.5008 -0.1150 -0.5011 -0.1693 -0.5015 -0.2275 -0.5019 -0.2898 -0.5023 -0.3564 -0.5028 -0.4274 -0.5033 -0.5029 -0.5038 -0.5829 -0.5044 -0.6676 -0.5050 -0.7569 -0.5057 -0.8509 -0.5064 -0.9495 -0.5071 -1.0529 -0.5079 -1.1610 -0.5089 -1.2741 -0.5099 -1.3925 -0.5112 -1.5167 -0.5128 -1.6476 -0.5147 -1.7867 -0.5174 -1.9359 -0.5210 -2.0983 -0.5263 -2.2788 -0.5344 -2.4842 -0.5472 -2.7251 -0.5680 -3.0182 -0.6026 -3.3900 -0.6607 -3.8849 -0.7543 -4.5802 -0.8915 -5.6192 -1.0701 -7.2543 -1.2662 -9.8844 -1.3867 -12.0474 -0.8957 -6.7716 0.5016 -1.3456 0.9957 0.4079 0.9156 0.9016 0.7363 0.9995 0.5940 0.9699 0.4664 0.9022 0.3753 0.8279 0.3011 0.7583 0.2438 0.6971 0.1989 0.6449 0.1635 0.6011 0.1354 0.5648 0.1129 0.5349 0.0945 0.5103 0.0791 0.4902 0.0658 0.4738 0.0539 0.4602 0.0426 0.4490 0.0314 0.4396 0.0200 0.4316 0.0079 0.4246 -0.0051 0.4184 -0.0194 0.4128 -0.0351 0.4076 -0.0524 0.4026 -0.0713 0.3979 -0.0921 0.3934 -0.1146 0.3890 -0.1389 0.3849 -0.1650 0.3811 -0.1927 0.3776 -0.2217 0.3746 -0.2518 0.3722 -0.2826 0.3705 -0.3135 0.3697 -0.3440 0.3701 -0.3732 0.3717 -0.4004 0.3748 -0.4248 0.3799 -0.4458 0.3873 -0.4629 0.3973 -0.4760 0.4106 -0.4854 0.4290 -0.4917 0.4541 -0.4954 0.4839 -0.4975 0.6045 -0.4984 -0.6687 -0.4989 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 14.000 0.166 0.636 -0.084 1.000 1.000 0.0000 -1.4054 Cpi Cpv ----------------- -0.6595 -0.5131 -0.5089 -0.5131 0.4628 -0.5131 0.4392 -0.5132 0.4118 -0.5132 0.3876 -0.5132 0.3634 -0.5132 0.3390 -0.5132 0.3145 -0.5132 0.2892 -0.5133 0.2629 -0.5134 0.2354 -0.5134 0.2062 -0.5135 0.1753 -0.5137 0.1422 -0.5138 0.1067 -0.5140 0.0687 -0.5142 0.0277 -0.5145 -0.0164 -0.5147 -0.0638 -0.5151 -0.1149 -0.5154 -0.1698 -0.5158 -0.2287 -0.5162 -0.2918 -0.5167 -0.3592 -0.5171 -0.4313 -0.5177 -0.5079 -0.5182 -0.5893 -0.5189 -0.6755 -0.5195 -0.7665 -0.5202 -0.8624 -0.5210 -0.9632 -0.5218 -1.0691 -0.5227 -1.1800 -0.5237 -1.2963 -0.5248 -1.4183 -0.5261 -1.5467 -0.5277 -1.6823 -0.5296 -1.8268 -0.5321 -1.9823 -0.5354 -2.1521 -0.5400 -2.3414 -0.5469 -2.5574 -0.5574 -2.8116 -0.5744 -3.1216 -0.6024 -3.5157 -0.6502 -4.0415 -0.7315 -4.7821 -0.8595 -5.8921 -1.0409 -7.6472 -1.2553 -10.4940 -1.4054 -12.9391 -0.9553 -7.4499 0.4581 -1.6245 0.9910 0.3018 0.9283 0.8665 0.7561 0.9958 0.6153 0.9808 0.4876 0.9200 0.3955 0.8488 0.3198 0.7803 0.2611 0.7191 0.2146 0.6663 0.1778 0.6217 0.1482 0.5843 0.1244 0.5533 0.1047 0.5277 0.0881 0.5065 0.0737 0.4890 0.0607 0.4745 0.0484 0.4624 0.0363 0.4521 0.0240 0.4434 0.0110 0.4357 -0.0029 0.4288 -0.0179 0.4226 -0.0344 0.4168 -0.0525 0.4113 -0.0722 0.4061 -0.0938 0.4012 -0.1171 0.3964 -0.1422 0.3919 -0.1691 0.3877 -0.1976 0.3839 -0.2275 0.3806 -0.2584 0.3779 -0.2901 0.3759 -0.3219 0.3748 -0.3532 0.3749 -0.3833 0.3763 -0.4113 0.3792 -0.4365 0.3841 -0.4581 0.3912 -0.4758 0.4011 -0.4894 0.4142 -0.4991 0.4324 -0.5056 0.4572 -0.5095 0.4868 -0.5116 0.6067 -0.5126 -0.6595 -0.5131 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 14.500 0.175 0.651 -0.087 1.000 1.000 0.0000 -1.4171 Cpi Cpv ----------------- -0.6501 -0.5268 -0.5004 -0.5268 0.4658 -0.5268 0.4423 -0.5268 0.4150 -0.5268 0.3909 -0.5268 0.3666 -0.5269 0.3423 -0.5269 0.3177 -0.5269 0.2924 -0.5270 0.2660 -0.5270 0.2384 -0.5271 0.2091 -0.5272 0.1779 -0.5274 0.1447 -0.5275 0.1090 -0.5277 0.0706 -0.5279 0.0293 -0.5282 -0.0151 -0.5284 -0.0630 -0.5288 -0.1146 -0.5291 -0.1701 -0.5295 -0.2296 -0.5299 -0.2935 -0.5304 -0.3619 -0.5309 -0.4349 -0.5315 -0.5127 -0.5321 -0.5954 -0.5327 -0.6831 -0.5334 -0.7758 -0.5342 -0.8737 -0.5350 -0.9767 -0.5359 -1.0850 -0.5368 -1.1988 -0.5379 -1.3183 -0.5391 -1.4439 -0.5404 -1.5764 -0.5420 -1.7168 -0.5439 -1.8667 -0.5463 -2.0286 -0.5494 -2.2059 -0.5536 -2.4041 -0.5596 -2.6309 -0.5685 -2.8985 -0.5825 -3.2257 -0.6055 -3.6426 -0.6448 -4.1999 -0.7134 -4.9868 -0.8295 -6.1695 -1.0074 -8.0480 -1.2362 -11.1184 -1.4171 -13.8581 -1.0088 -8.1553 0.4146 -1.9186 0.9849 0.1872 0.9399 0.8262 0.7751 0.9885 0.6359 0.9893 0.5084 0.9361 0.4154 0.8684 0.3384 0.8013 0.2783 0.7404 0.2304 0.6872 0.1921 0.6417 0.1612 0.6034 0.1360 0.5714 0.1151 0.5447 0.0974 0.5225 0.0819 0.5041 0.0678 0.4887 0.0545 0.4757 0.0415 0.4646 0.0283 0.4551 0.0145 0.4467 -0.0002 0.4392 -0.0161 0.4324 -0.0334 0.4260 -0.0523 0.4200 -0.0728 0.4144 -0.0951 0.4090 -0.1192 0.4038 -0.1451 0.3989 -0.1728 0.3943 -0.2021 0.3902 -0.2328 0.3866 -0.2646 0.3836 -0.2971 0.3813 -0.3298 0.3800 -0.3619 0.3799 -0.3928 0.3810 -0.4217 0.3837 -0.4476 0.3883 -0.4699 0.3953 -0.4881 0.4049 -0.5022 0.4178 -0.5123 0.4358 -0.5189 0.4604 -0.5230 0.4898 -0.5252 0.6089 -0.5263 -0.6501 -0.5268 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 15.000 0.190 0.691 -0.098 0.961 1.000 0.0000 -1.4488 Cpi Cpv ----------------- -0.6404 -0.5190 -0.4917 -0.5190 0.4689 -0.5190 0.4455 -0.5190 0.4183 -0.5191 0.3942 -0.5194 0.3700 -0.5198 0.3457 -0.5204 0.3211 -0.5214 0.2956 -0.5229 0.2693 -0.5250 0.2415 -0.5278 0.2121 -0.5315 0.1808 -0.5366 0.1473 -0.5435 0.1114 -0.5534 0.0727 -0.5596 0.0311 -0.5598 -0.0137 -0.5601 -0.0621 -0.5605 -0.1141 -0.5608 -0.1702 -0.5613 -0.2304 -0.5617 -0.2951 -0.5622 -0.3643 -0.5628 -0.4384 -0.5634 -0.5173 -0.5640 -0.6013 -0.5647 -0.6905 -0.5655 -0.7849 -0.5663 -0.8847 -0.5672 -0.9899 -0.5681 -1.1007 -0.5692 -1.2173 -0.5704 -1.3400 -0.5716 -1.4692 -0.5731 -1.6059 -0.5748 -1.7510 -0.5768 -1.9065 -0.5792 -2.0747 -0.5822 -2.2596 -0.5861 -2.4668 -0.5915 -2.7046 -0.5991 -2.9858 -0.6107 -3.3304 -0.6292 -3.7704 -0.6605 -4.3599 -0.7158 -5.1940 -0.8155 -6.4513 -0.9828 -8.4565 -1.2249 -11.7574 -1.4488 -14.8041 -1.0984 -8.8874 0.3443 -2.2278 0.9729 0.0639 0.9550 0.7805 0.8014 0.9778 0.6650 0.9954 0.5382 0.9504 0.4443 0.8867 0.3658 0.8213 0.3041 0.7608 0.2546 0.7073 0.2147 0.6613 0.1823 0.6222 0.1557 0.5892 0.1335 0.5616 0.1145 0.5384 0.0979 0.5190 0.0828 0.5027 0.0686 0.4889 0.0548 0.4770 0.0408 0.4668 0.0263 0.4577 0.0109 0.4496 -0.0055 0.4421 -0.0233 0.4353 -0.0426 0.4288 -0.0635 0.4226 -0.0862 0.4168 -0.1106 0.4112 -0.1368 0.4060 -0.1646 0.4011 -0.1941 0.3966 -0.2249 0.3926 -0.2568 0.3894 -0.2894 0.3868 -0.3221 0.3853 -0.3542 0.3848 -0.3851 0.3858 -0.4139 0.3882 -0.4398 0.3927 -0.4621 0.3994 -0.4803 0.4088 -0.4943 0.4215 -0.5044 0.4393 -0.5111 0.4637 -0.5151 0.4929 -0.5174 0.6112 -0.5184 -0.6404 -0.5190 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 15.500 0.203 0.719 -0.104 0.921 1.000 0.0000 -1.4580 Cpi Cpv ----------------- -0.6306 -0.5147 -0.4827 -0.5147 0.4720 -0.5147 0.4488 -0.5148 0.4216 -0.5149 0.3976 -0.5150 0.3734 -0.5153 0.3491 -0.5159 0.3245 -0.5166 0.2990 -0.5177 0.2726 -0.5192 0.2447 -0.5212 0.2152 -0.5239 0.1837 -0.5274 0.1501 -0.5318 0.1139 -0.5375 0.0750 -0.5449 0.0330 -0.5545 -0.0122 -0.5680 -0.0610 -0.5833 -0.1135 -0.5837 -0.1701 -0.5841 -0.2310 -0.5846 -0.2964 -0.5852 -0.3666 -0.5857 -0.4416 -0.5863 -0.5217 -0.5870 -0.6070 -0.5878 -0.6976 -0.5886 -0.7937 -0.5894 -0.8954 -0.5904 -1.0028 -0.5914 -1.1161 -0.5925 -1.2355 -0.5938 -1.3614 -0.5951 -1.4943 -0.5967 -1.6351 -0.5984 -1.7851 -0.6005 -1.9461 -0.6029 -2.1208 -0.6059 -2.3133 -0.6097 -2.5296 -0.6146 -2.7785 -0.6214 -3.0735 -0.6314 -3.4358 -0.6469 -3.8993 -0.6726 -4.5215 -0.7179 -5.4038 -0.8020 -6.7373 -0.9545 -8.8725 -1.1987 -12.4109 -1.4580 -15.7768 -1.1630 -9.6462 0.2845 -2.5521 0.9601 -0.0679 0.9662 0.7295 0.8229 0.9635 0.6893 0.9989 0.5635 0.9629 0.4690 0.9036 0.3894 0.8402 0.3264 0.7804 0.2755 0.7269 0.2342 0.6803 0.2004 0.6405 0.1725 0.6067 0.1491 0.5781 0.1291 0.5541 0.1114 0.5338 0.0954 0.5166 0.0804 0.5020 0.0657 0.4894 0.0510 0.4784 0.0358 0.4687 0.0198 0.4599 0.0028 0.4519 -0.0155 0.4445 -0.0352 0.4375 -0.0566 0.4309 -0.0796 0.4247 -0.1043 0.4187 -0.1308 0.4131 -0.1590 0.4078 -0.1887 0.4030 -0.2197 0.3988 -0.2518 0.3952 -0.2844 0.3924 -0.3173 0.3906 -0.3495 0.3899 -0.3805 0.3906 -0.4094 0.3929 -0.4353 0.3971 -0.4576 0.4036 -0.4759 0.4128 -0.4900 0.4253 -0.5001 0.4429 -0.5068 0.4671 -0.5109 0.4960 -0.5131 0.6136 -0.5142 -0.6306 -0.5147 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 16.000 0.215 0.742 -0.109 0.870 1.000 0.0000 -1.4546 Cpi Cpv ----------------- -0.6205 -0.5078 -0.4736 -0.5078 0.4753 -0.5079 0.4521 -0.5079 0.4251 -0.5079 0.4011 -0.5081 0.3770 -0.5083 0.3527 -0.5087 0.3280 -0.5093 0.3025 -0.5102 0.2760 -0.5114 0.2480 -0.5130 0.2184 -0.5151 0.1868 -0.5177 0.1529 -0.5210 0.1165 -0.5252 0.0773 -0.5304 0.0351 -0.5368 -0.0105 -0.5448 -0.0597 -0.5549 -0.1127 -0.5681 -0.1699 -0.5868 -0.2315 -0.6037 -0.2976 -0.6043 -0.3686 -0.6049 -0.4446 -0.6055 -0.5258 -0.6062 -0.6124 -0.6070 -0.7045 -0.6078 -0.8023 -0.6087 -0.9059 -0.6097 -1.0155 -0.6108 -1.1312 -0.6119 -1.2535 -0.6132 -1.3826 -0.6147 -1.5191 -0.6163 -1.6642 -0.6181 -1.8189 -0.6202 -1.9855 -0.6227 -2.1667 -0.6257 -2.3669 -0.6293 -2.5924 -0.6340 -2.8525 -0.6403 -3.1614 -0.6491 -3.5417 -0.6624 -4.0291 -0.6840 -4.6847 -0.7217 -5.6162 -0.7923 -7.0275 -0.9284 -9.2959 -1.1661 -13.0786 -1.4546 -16.7759 -1.2160 -10.4313 0.2279 -2.8914 0.9461 -0.2082 0.9753 0.6732 0.8423 0.9458 0.7117 1.0000 0.5872 0.9736 0.4924 0.9192 0.4119 0.8581 0.3478 0.7992 0.2956 0.7458 0.2531 0.6989 0.2181 0.6584 0.1890 0.6238 0.1645 0.5944 0.1435 0.5695 0.1249 0.5484 0.1080 0.5304 0.0921 0.5150 0.0767 0.5017 0.0613 0.4900 0.0456 0.4796 0.0291 0.4703 0.0115 0.4617 -0.0072 0.4538 -0.0273 0.4463 -0.0490 0.4393 -0.0723 0.4326 -0.0973 0.4262 -0.1240 0.4202 -0.1523 0.4146 -0.1821 0.4095 -0.2132 0.4050 -0.2453 0.4011 -0.2780 0.3980 -0.3108 0.3960 -0.3430 0.3951 -0.3739 0.3955 -0.4027 0.3975 -0.4286 0.4016 -0.4508 0.4078 -0.4690 0.4169 -0.4831 0.4292 -0.4932 0.4466 -0.4998 0.4705 -0.5039 0.4992 -0.5062 0.6160 -0.5073 -0.6205 -0.5078 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 16.500 0.227 0.761 -0.112 0.834 1.000 0.0000 -1.4424 Cpi Cpv ----------------- -0.6102 -0.5071 -0.4642 -0.5071 0.4786 -0.5071 0.4555 -0.5071 0.4286 -0.5072 0.4047 -0.5073 0.3806 -0.5075 0.3563 -0.5079 0.3317 -0.5084 0.3061 -0.5092 0.2795 -0.5103 0.2515 -0.5117 0.2217 -0.5135 0.1899 -0.5158 0.1559 -0.5188 0.1193 -0.5224 0.0799 -0.5268 0.0373 -0.5322 -0.0086 -0.5388 -0.0582 -0.5469 -0.1118 -0.5569 -0.1695 -0.5695 -0.2317 -0.5862 -0.2986 -0.6121 -0.3704 -0.6213 -0.4474 -0.6220 -0.5297 -0.6227 -0.6176 -0.6235 -0.7112 -0.6243 -0.8106 -0.6253 -0.9162 -0.6263 -1.0279 -0.6274 -1.1461 -0.6286 -1.2711 -0.6299 -1.4035 -0.6314 -1.5437 -0.6331 -1.6929 -0.6350 -1.8525 -0.6371 -2.0247 -0.6397 -2.2125 -0.6426 -2.4204 -0.6462 -2.6552 -0.6507 -2.9266 -0.6566 -3.2497 -0.6646 -3.6481 -0.6764 -4.1599 -0.6949 -4.8493 -0.7268 -5.8309 -0.7865 -7.3218 -0.9063 -9.7266 -1.1319 -13.7603 -1.4424 -17.8012 -1.2598 -11.2426 0.1744 -3.2455 0.9311 -0.3569 0.9825 0.6117 0.8596 0.9245 0.7322 0.9986 0.6091 0.9824 0.5140 0.9334 0.4327 0.8750 0.3676 0.8172 0.3143 0.7641 0.2706 0.7170 0.2345 0.6759 0.2043 0.6407 0.1787 0.6105 0.1566 0.5848 0.1371 0.5629 0.1193 0.5441 0.1026 0.5279 0.0865 0.5139 0.0704 0.5015 0.0539 0.4905 0.0368 0.4806 0.0187 0.4715 -0.0005 0.4630 -0.0212 0.4551 -0.0433 0.4476 -0.0671 0.4405 -0.0925 0.4338 -0.1196 0.4275 -0.1482 0.4215 -0.1784 0.4161 -0.2098 0.4112 -0.2422 0.4071 -0.2752 0.4038 -0.3082 0.4014 -0.3407 0.4003 -0.3719 0.4005 -0.4009 0.4023 -0.4270 0.4061 -0.4494 0.4122 -0.4678 0.4210 -0.4820 0.4331 -0.4922 0.4503 -0.4990 0.4740 -0.5031 0.5024 -0.5054 0.6185 -0.5065 -0.6102 -0.5071 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 17.000 0.238 0.774 -0.114 0.805 1.000 0.0000 -1.4182 Cpi Cpv ----------------- -0.5997 -0.5074 -0.4547 -0.5074 0.4819 -0.5074 0.4590 -0.5074 0.4321 -0.5075 0.4083 -0.5076 0.3843 -0.5078 0.3600 -0.5081 0.3354 -0.5086 0.3098 -0.5093 0.2831 -0.5103 0.2550 -0.5116 0.2251 -0.5132 0.1932 -0.5154 0.1590 -0.5180 0.1222 -0.5213 0.0825 -0.5253 0.0397 -0.5301 -0.0066 -0.5359 -0.0566 -0.5429 -0.1106 -0.5515 -0.1689 -0.5619 -0.2317 -0.5750 -0.2994 -0.5921 -0.3720 -0.6178 -0.4500 -0.6321 -0.5334 -0.6329 -0.6226 -0.6337 -0.7176 -0.6345 -0.8187 -0.6355 -0.9261 -0.6365 -1.0400 -0.6376 -1.1607 -0.6389 -1.2885 -0.6402 -1.4241 -0.6417 -1.5680 -0.6434 -1.7214 -0.6454 -1.8859 -0.6475 -2.0637 -0.6501 -2.2581 -0.6530 -2.4738 -0.6566 -2.7179 -0.6610 -3.0008 -0.6665 -3.3382 -0.6740 -3.7551 -0.6846 -4.2915 -0.7008 -5.0154 -0.7283 -6.0481 -0.7793 -7.6202 -0.8841 -10.1644 -1.0944 -14.4558 -1.4182 -18.8522 -1.2889 -12.0797 0.1278 -3.6143 0.9163 -0.5141 0.9880 0.5450 0.8745 0.8997 0.7502 0.9948 0.6288 0.9895 0.5336 0.9462 0.4517 0.8908 0.3858 0.8344 0.3315 0.7817 0.2867 0.7345 0.2495 0.6930 0.2183 0.6572 0.1917 0.6263 0.1687 0.5998 0.1483 0.5771 0.1297 0.5576 0.1122 0.5407 0.0953 0.5260 0.0785 0.5130 0.0615 0.5014 0.0438 0.4909 0.0251 0.4812 0.0053 0.4723 -0.0158 0.4639 -0.0384 0.4560 -0.0626 0.4485 -0.0884 0.4414 -0.1159 0.4347 -0.1449 0.4284 -0.1754 0.4227 -0.2072 0.4175 -0.2399 0.4131 -0.2732 0.4095 -0.3066 0.4069 -0.3393 0.4056 -0.3707 0.4055 -0.4000 0.4071 -0.4263 0.4107 -0.4490 0.4166 -0.4676 0.4253 -0.4819 0.4372 -0.4922 0.4541 -0.4991 0.4775 -0.5033 0.5057 -0.5056 0.6210 -0.5068 -0.5997 -0.5074 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 17.500 0.249 0.786 -0.116 0.779 1.000 0.0000 -1.3899 Cpi Cpv ----------------- -0.5889 -0.5078 -0.4450 -0.5078 0.4854 -0.5078 0.4625 -0.5078 0.4358 -0.5078 0.4121 -0.5080 0.3881 -0.5081 0.3638 -0.5084 0.3392 -0.5089 0.3136 -0.5096 0.2869 -0.5105 0.2586 -0.5116 0.2287 -0.5132 0.1966 -0.5151 0.1623 -0.5176 0.1252 -0.5206 0.0853 -0.5243 0.0422 -0.5287 -0.0045 -0.5341 -0.0549 -0.5404 -0.1093 -0.5480 -0.1681 -0.5572 -0.2316 -0.5684 -0.2999 -0.5823 -0.3734 -0.6006 -0.4523 -0.6285 -0.5369 -0.6426 -0.6273 -0.6434 -0.7237 -0.6443 -0.8265 -0.6452 -0.9358 -0.6463 -1.0519 -0.6474 -1.1750 -0.6487 -1.3057 -0.6500 -1.4444 -0.6516 -1.5920 -0.6533 -1.7497 -0.6552 -1.9191 -0.6574 -2.1025 -0.6600 -2.3036 -0.6629 -2.5271 -0.6665 -2.7807 -0.6707 -3.0751 -0.6761 -3.4270 -0.6831 -3.8626 -0.6928 -4.4239 -0.7073 -5.1829 -0.7312 -6.2675 -0.7752 -7.9224 -0.8663 -10.6093 -1.0599 -15.1650 -1.3899 -19.9287 -1.3145 -12.9425 0.0806 -3.9978 0.9002 -0.6796 0.9924 0.4730 0.8887 0.8715 0.7677 0.9885 0.6482 0.9948 0.5530 0.9577 0.4707 0.9056 0.4040 0.8508 0.3488 0.7987 0.3030 0.7515 0.2648 0.7097 0.2325 0.6733 0.2050 0.6418 0.1810 0.6147 0.1597 0.5912 0.1403 0.5710 0.1221 0.5534 0.1045 0.5380 0.0870 0.5244 0.0693 0.5122 0.0510 0.5011 0.0319 0.4910 0.0116 0.4816 -0.0101 0.4727 -0.0331 0.4644 -0.0578 0.4565 -0.0840 0.4490 -0.1119 0.4420 -0.1413 0.4354 -0.1722 0.4293 -0.2043 0.4239 -0.2374 0.4192 -0.2710 0.4153 -0.3047 0.4125 -0.3377 0.4109 -0.3695 0.4107 -0.3990 0.4120 -0.4256 0.4154 -0.4485 0.4211 -0.4673 0.4295 -0.4818 0.4412 -0.4923 0.4580 -0.4993 0.4812 -0.5035 0.5091 -0.5059 0.6235 -0.5072 -0.5889 -0.5078 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 18.000 0.260 0.796 -0.118 0.748 1.000 0.0000 -1.3566 Cpi Cpv ----------------- -0.5780 -0.5057 -0.4351 -0.5057 0.4889 -0.5057 0.4661 -0.5057 0.4395 -0.5058 0.4159 -0.5059 0.3919 -0.5060 0.3677 -0.5063 0.3431 -0.5067 0.3174 -0.5073 0.2907 -0.5082 0.2624 -0.5093 0.2323 -0.5107 0.2001 -0.5125 0.1656 -0.5147 0.1284 -0.5175 0.0882 -0.5209 0.0448 -0.5249 -0.0021 -0.5298 -0.0529 -0.5356 -0.1079 -0.5424 -0.1672 -0.5505 -0.2313 -0.5602 -0.3003 -0.5720 -0.3746 -0.5866 -0.4545 -0.6058 -0.5401 -0.6348 -0.6318 -0.6510 -0.7297 -0.6519 -0.8341 -0.6528 -0.9452 -0.6539 -1.0634 -0.6550 -1.1890 -0.6563 -1.3225 -0.6577 -1.4645 -0.6592 -1.6158 -0.6610 -1.7777 -0.6629 -1.9519 -0.6651 -2.1411 -0.6677 -2.3488 -0.6706 -2.5803 -0.6741 -2.8434 -0.6783 -3.1495 -0.6835 -3.5160 -0.6902 -3.9705 -0.6992 -4.5572 -0.7123 -5.3517 -0.7334 -6.4892 -0.7716 -8.2285 -0.8509 -11.0611 -1.0276 -15.8875 -1.3566 -21.0304 -1.3339 -13.8306 0.0347 -4.3958 0.8832 -0.8535 0.9958 0.3958 0.9019 0.8397 0.7845 0.9797 0.6671 0.9982 0.5720 0.9678 0.4895 0.9193 0.4221 0.8663 0.3661 0.8151 0.3194 0.7680 0.2802 0.7260 0.2470 0.6891 0.2186 0.6571 0.1938 0.6293 0.1717 0.6052 0.1515 0.5843 0.1325 0.5660 0.1143 0.5500 0.0962 0.5357 0.0779 0.5230 0.0591 0.5114 0.0394 0.5007 0.0186 0.4908 -0.0034 0.4816 -0.0269 0.4728 -0.0519 0.4645 -0.0785 0.4567 -0.1067 0.4493 -0.1364 0.4424 -0.1675 0.4360 -0.1999 0.4303 -0.2332 0.4254 -0.2671 0.4212 -0.3010 0.4182 -0.3343 0.4163 -0.3662 0.4159 -0.3960 0.4170 -0.4228 0.4202 -0.4458 0.4257 -0.4648 0.4339 -0.4794 0.4454 -0.4900 0.4619 -0.4970 0.4849 -0.5014 0.5125 -0.5038 0.6261 -0.5050 -0.5780 -0.5057 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 18.500 0.270 0.805 -0.118 0.711 1.000 0.0000 -1.3485 Cpi Cpv ----------------- -0.5669 -0.5006 -0.4250 -0.5006 0.4924 -0.5006 0.4698 -0.5006 0.4433 -0.5007 0.4198 -0.5008 0.3959 -0.5009 0.3717 -0.5012 0.3470 -0.5016 0.3214 -0.5021 0.2946 -0.5029 0.2663 -0.5039 0.2361 -0.5052 0.2038 -0.5069 0.1691 -0.5089 0.1317 -0.5115 0.0913 -0.5145 0.0476 -0.5182 0.0003 -0.5226 -0.0509 -0.5278 -0.1062 -0.5339 -0.1661 -0.5412 -0.2308 -0.5497 -0.3005 -0.5598 -0.3756 -0.5720 -0.4564 -0.5870 -0.5431 -0.6064 -0.6360 -0.6348 -0.7353 -0.6584 -0.8414 -0.6593 -0.9544 -0.6604 -1.0747 -0.6615 -1.2028 -0.6628 -1.3391 -0.6642 -1.4842 -0.6658 -1.6392 -0.6675 -1.8054 -0.6695 -1.9845 -0.6717 -2.1794 -0.6742 -2.3938 -0.6772 -2.6333 -0.6806 -2.9060 -0.6848 -3.2239 -0.6898 -3.6052 -0.6962 -4.0789 -0.7046 -4.6912 -0.7166 -5.5219 -0.7355 -6.7131 -0.7690 -8.5383 -0.8380 -11.5196 -0.9982 -16.6232 -1.3196 -22.1569 -1.3485 -14.7438 -0.0109 -4.8082 0.8650 -1.0356 0.9982 0.3135 0.9145 0.8045 0.8008 0.9685 0.6859 0.9999 0.5909 0.9765 0.5083 0.9319 0.4405 0.8810 0.3836 0.8307 0.3361 0.7839 0.2961 0.7418 0.2621 0.7046 0.2328 0.6720 0.2071 0.6436 0.1843 0.6189 0.1634 0.5974 0.1437 0.5785 0.1249 0.5618 0.1062 0.5470 0.0875 0.5337 0.0682 0.5216 0.0480 0.5104 0.0269 0.5001 0.0045 0.4904 -0.0193 0.4812 -0.0446 0.4726 -0.0715 0.4644 -0.0999 0.4567 -0.1298 0.4494 -0.1611 0.4428 -0.1936 0.4368 -0.2271 0.4316 -0.2611 0.4272 -0.2951 0.4239 -0.3285 0.4218 -0.3605 0.4211 -0.3904 0.4221 -0.4172 0.4250 -0.4404 0.4303 -0.4594 0.4383 -0.4741 0.4496 -0.4847 0.4659 -0.4918 0.4886 -0.4962 0.5160 -0.4987 0.6288 -0.4999 -0.5669 -0.5006 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 19.000 0.280 0.810 -0.119 0.682 1.000 0.0000 -1.3530 Cpi Cpv ----------------- -0.5556 -0.4950 -0.4147 -0.4950 0.4961 -0.4950 0.4735 -0.4951 0.4472 -0.4951 0.4237 -0.4952 0.3999 -0.4953 0.3757 -0.4956 0.3511 -0.4959 0.3255 -0.4965 0.2986 -0.4972 0.2702 -0.4981 0.2399 -0.4993 0.2075 -0.5009 0.1727 -0.5028 0.1351 -0.5051 0.0945 -0.5080 0.0505 -0.5114 0.0029 -0.5154 -0.0486 -0.5202 -0.1044 -0.5259 -0.1648 -0.5325 -0.2301 -0.5402 -0.3005 -0.5494 -0.3764 -0.5601 -0.4581 -0.5731 -0.5459 -0.5890 -0.6400 -0.6097 -0.7407 -0.6411 -0.8484 -0.6613 -0.9633 -0.6624 -1.0857 -0.6635 -1.2162 -0.6648 -1.3553 -0.6662 -1.5037 -0.6677 -1.6623 -0.6695 -1.8328 -0.6714 -2.0169 -0.6736 -2.2175 -0.6762 -2.4387 -0.6791 -2.6861 -0.6825 -2.9685 -0.6866 -3.2983 -0.6915 -3.6946 -0.6977 -4.1876 -0.7057 -4.8260 -0.7168 -5.6932 -0.7338 -6.9390 -0.7634 -8.8517 -0.8239 -11.9847 -0.9681 -17.3718 -1.2768 -23.3079 -1.3530 -15.6818 -0.0517 -5.2348 0.8470 -1.2260 0.9995 0.2260 0.9258 0.7658 0.8156 0.9548 0.7036 0.9997 0.6086 0.9839 0.5263 0.9435 0.4580 0.8949 0.4006 0.8457 0.3523 0.7994 0.3115 0.7572 0.2767 0.7197 0.2467 0.6867 0.2203 0.6578 0.1967 0.6325 0.1751 0.6103 0.1549 0.5909 0.1355 0.5736 0.1163 0.5582 0.0970 0.5444 0.0773 0.5318 0.0568 0.5201 0.0353 0.5093 0.0125 0.4992 -0.0116 0.4897 -0.0371 0.4806 -0.0642 0.4721 -0.0928 0.4640 -0.1229 0.4565 -0.1544 0.4496 -0.1870 0.4433 -0.2206 0.4378 -0.2547 0.4332 -0.2888 0.4296 -0.3223 0.4273 -0.3544 0.4264 -0.3843 0.4272 -0.4112 0.4299 -0.4345 0.4350 -0.4535 0.4428 -0.4683 0.4539 -0.4789 0.4700 -0.4861 0.4924 -0.4905 0.5196 -0.4931 0.6315 -0.4944 -0.5556 -0.4950 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 19.500 0.295 0.829 -0.121 0.660 1.000 0.0000 -1.3658 Cpi Cpv ----------------- -0.5441 -0.4968 -0.4043 -0.4968 0.4998 -0.4968 0.4774 -0.4968 0.4512 -0.4969 0.4278 -0.4970 0.4040 -0.4971 0.3799 -0.4973 0.3553 -0.4977 0.3296 -0.4982 0.3027 -0.4989 0.2743 -0.4998 0.2439 -0.5010 0.2114 -0.5026 0.1764 -0.5044 0.1386 -0.5067 0.0978 -0.5095 0.0536 -0.5129 0.0057 -0.5168 -0.0462 -0.5215 -0.1024 -0.5270 -0.1633 -0.5335 -0.2292 -0.5410 -0.3003 -0.5499 -0.3770 -0.5603 -0.4596 -0.5727 -0.5484 -0.5877 -0.6437 -0.6064 -0.7458 -0.6313 -0.8551 -0.6762 -0.9719 -0.6817 -1.0964 -0.6828 -1.2294 -0.6841 -1.3712 -0.6855 -1.5228 -0.6871 -1.6852 -0.6888 -1.8599 -0.6908 -2.0489 -0.6931 -2.2553 -0.6956 -2.4832 -0.6986 -2.7388 -0.7020 -3.0309 -0.7061 -3.3727 -0.7110 -3.7841 -0.7170 -4.2967 -0.7247 -4.9614 -0.7352 -5.8658 -0.7507 -7.1670 -0.7770 -9.1687 -0.8298 -12.4563 -0.9574 -18.1332 -1.2510 -24.4830 -1.3658 -16.6444 -0.1283 -5.6756 0.8338 -1.4245 1.0000 0.1334 0.9418 0.7237 0.8289 0.9386 0.7255 0.9977 0.6266 0.9899 0.5467 0.9540 0.4771 0.9079 0.4190 0.8600 0.3698 0.8142 0.3281 0.7722 0.2923 0.7345 0.2613 0.7011 0.2340 0.6717 0.2095 0.6458 0.1871 0.6231 0.1661 0.6031 0.1460 0.5853 0.1261 0.5694 0.1062 0.5550 0.0858 0.5419 0.0647 0.5298 0.0426 0.5186 0.0194 0.5080 -0.0052 0.4981 -0.0313 0.4887 -0.0589 0.4798 -0.0880 0.4715 -0.1185 0.4636 -0.1505 0.4564 -0.1836 0.4498 -0.2177 0.4441 -0.2523 0.4392 -0.2869 0.4355 -0.3209 0.4329 -0.3535 0.4318 -0.3839 0.4323 -0.4113 0.4349 -0.4349 0.4397 -0.4544 0.4474 -0.4694 0.4583 -0.4803 0.4741 -0.4876 0.4963 -0.4922 0.5232 -0.4948 0.6343 -0.4961 -0.5441 -0.4968 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 20.000 0.299 0.819 -0.119 0.635 1.000 0.0000 -1.3311 Cpi Cpv ----------------- -0.5323 -0.4828 -0.3937 -0.4828 0.5035 -0.4828 0.4812 -0.4829 0.4552 -0.4829 0.4319 -0.4830 0.4082 -0.4831 0.3841 -0.4833 0.3595 -0.4836 0.3338 -0.4841 0.3069 -0.4848 0.2784 -0.4856 0.2480 -0.4867 0.2154 -0.4881 0.1802 -0.4898 0.1423 -0.4919 0.1012 -0.4945 0.0568 -0.4975 0.0086 -0.5011 -0.0437 -0.5054 -0.1003 -0.5103 -0.1617 -0.5162 -0.2281 -0.5229 -0.2999 -0.5308 -0.3773 -0.5401 -0.4608 -0.5510 -0.5507 -0.5639 -0.6472 -0.5796 -0.7507 -0.5996 -0.8616 -0.6275 -0.9802 -0.6651 -1.1069 -0.6662 -1.2422 -0.6675 -1.3869 -0.6688 -1.5417 -0.6704 -1.7077 -0.6721 -1.8866 -0.6740 -2.0806 -0.6762 -2.2928 -0.6787 -2.5276 -0.6816 -2.7913 -0.6849 -3.0932 -0.6889 -3.4470 -0.6936 -3.8737 -0.6994 -4.4061 -0.7067 -5.0975 -0.7165 -6.0395 -0.7307 -7.3970 -0.7544 -9.4891 -0.8013 -12.9342 -0.9153 -18.9070 -1.1904 -25.6818 -1.3311 -17.6312 -0.1521 -6.1304 0.8221 -1.6310 0.9996 0.0357 0.9490 0.6781 0.8406 0.9200 0.7394 0.9939 0.6417 0.9945 0.5622 0.9634 0.4927 0.9201 0.4343 0.8737 0.3848 0.8286 0.3426 0.7867 0.3063 0.7489 0.2748 0.7152 0.2470 0.6853 0.2221 0.6590 0.1993 0.6358 0.1779 0.6152 0.1574 0.5969 0.1372 0.5804 0.1170 0.5656 0.0964 0.5520 0.0752 0.5394 0.0530 0.5278 0.0296 0.5168 0.0050 0.5065 -0.0210 0.4968 -0.0485 0.4876 -0.0775 0.4789 -0.1080 0.4708 -0.1397 0.4633 -0.1726 0.4565 -0.2064 0.4505 -0.2407 0.4454 -0.2750 0.4413 -0.3086 0.4386 -0.3409 0.4373 -0.3710 0.4376 -0.3981 0.4399 -0.4215 0.4446 -0.4407 0.4520 -0.4555 0.4627 -0.4663 0.4783 -0.4736 0.5003 -0.4781 0.5269 -0.4807 0.6371 -0.4821 -0.5323 -0.4828 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 20.500 0.305 0.811 -0.118 0.618 1.000 0.0000 -1.3019 Cpi Cpv ----------------- -0.5204 -0.4697 -0.3829 -0.4697 0.5073 -0.4698 0.4852 -0.4698 0.4593 -0.4698 0.4360 -0.4699 0.4124 -0.4700 0.3884 -0.4702 0.3638 -0.4705 0.3382 -0.4710 0.3112 -0.4716 0.2827 -0.4724 0.2522 -0.4734 0.2194 -0.4747 0.1842 -0.4763 0.1461 -0.4783 0.1048 -0.4807 0.0601 -0.4835 0.0116 -0.4869 -0.0410 -0.4909 -0.0980 -0.4955 -0.1599 -0.5009 -0.2268 -0.5072 -0.2992 -0.5145 -0.3775 -0.5231 -0.4619 -0.5331 -0.5528 -0.5448 -0.6505 -0.5589 -0.7553 -0.5764 -0.8678 -0.5993 -0.9882 -0.6373 -1.1170 -0.6505 -1.2548 -0.6517 -1.4022 -0.6531 -1.5602 -0.6546 -1.7299 -0.6562 -1.9131 -0.6581 -2.1121 -0.6602 -2.3300 -0.6627 -2.5717 -0.6655 -2.8435 -0.6687 -3.1553 -0.6726 -3.5213 -0.6771 -3.9634 -0.6827 -4.5158 -0.6897 -5.2342 -0.6989 -6.2143 -0.7121 -7.6289 -0.7335 -9.8129 -0.7753 -13.4184 -0.8770 -19.6931 -1.1331 -26.9040 -1.3019 -18.6419 -0.1755 -6.5991 0.8080 -1.8456 0.9985 -0.0670 0.9559 0.6291 0.8524 0.8990 0.7534 0.9883 0.6570 0.9977 0.5780 0.9718 0.5085 0.9314 0.4500 0.8866 0.4001 0.8423 0.3574 0.8008 0.3207 0.7629 0.2887 0.7290 0.2604 0.6988 0.2350 0.6720 0.2118 0.6483 0.1900 0.6272 0.1691 0.6083 0.1486 0.5914 0.1281 0.5761 0.1073 0.5620 0.0859 0.5491 0.0636 0.5370 0.0401 0.5257 0.0154 0.5150 -0.0106 0.5049 -0.0381 0.4954 -0.0670 0.4864 -0.0973 0.4780 -0.1289 0.4702 -0.1617 0.4631 -0.1953 0.4569 -0.2293 0.4515 -0.2634 0.4473 -0.2967 0.4443 -0.3288 0.4428 -0.3586 0.4429 -0.3855 0.4450 -0.4087 0.4495 -0.4277 0.4567 -0.4425 0.4672 -0.4532 0.4826 -0.4605 0.5043 -0.4650 0.5307 -0.4676 0.6399 -0.4690 -0.5204 -0.4697 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 21.000 0.316 0.823 -0.119 0.594 1.000 0.0000 -1.3113 Cpi Cpv ----------------- -0.5084 -0.4655 -0.3719 -0.4655 0.5112 -0.4655 0.4892 -0.4655 0.4634 -0.4655 0.4403 -0.4656 0.4167 -0.4657 0.3928 -0.4659 0.3682 -0.4662 0.3426 -0.4666 0.3156 -0.4672 0.2870 -0.4680 0.2564 -0.4690 0.2236 -0.4703 0.1883 -0.4718 0.1500 -0.4738 0.1085 -0.4761 0.0636 -0.4788 0.0148 -0.4821 -0.0381 -0.4860 -0.0955 -0.4905 -0.1579 -0.4957 -0.2254 -0.5018 -0.2984 -0.5088 -0.3774 -0.5170 -0.4627 -0.5266 -0.5546 -0.5378 -0.6535 -0.5511 -0.7597 -0.5671 -0.8737 -0.5874 -0.9959 -0.6151 -1.1268 -0.6618 -1.2670 -0.6631 -1.4172 -0.6644 -1.5784 -0.6659 -1.7518 -0.6676 -1.9393 -0.6694 -2.1432 -0.6716 -2.3670 -0.6740 -2.6155 -0.6768 -2.8955 -0.6800 -3.2173 -0.6838 -3.5956 -0.6884 -4.0531 -0.6939 -4.6257 -0.7007 -5.3714 -0.7095 -6.3901 -0.7219 -7.8626 -0.7414 -10.1399 -0.7789 -13.9085 -0.8693 -20.4912 -1.1080 -28.1493 -1.3113 -19.6763 -0.2292 -7.0814 0.7833 -2.0682 0.9958 -0.1748 0.9647 0.5767 0.8672 0.8755 0.7707 0.9809 0.6755 0.9995 0.5968 0.9790 0.5270 0.9419 0.4679 0.8989 0.4173 0.8556 0.3739 0.8144 0.3364 0.7766 0.3036 0.7425 0.2746 0.7119 0.2485 0.6848 0.2246 0.6606 0.2021 0.6390 0.1807 0.6197 0.1596 0.6023 0.1387 0.5865 0.1174 0.5720 0.0955 0.5586 0.0728 0.5462 0.0490 0.5345 0.0239 0.5234 -0.0024 0.5130 -0.0302 0.5032 -0.0594 0.4939 -0.0900 0.4852 -0.1219 0.4771 -0.1549 0.4698 -0.1887 0.4633 -0.2230 0.4577 -0.2572 0.4533 -0.2909 0.4501 -0.3231 0.4483 -0.3532 0.4482 -0.3803 0.4502 -0.4037 0.4544 -0.4229 0.4615 -0.4378 0.4717 -0.4487 0.4869 -0.4560 0.5083 -0.4606 0.5344 -0.4633 0.6428 -0.4647 -0.5084 -0.4655 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 21.500 0.307 0.781 -0.112 0.578 1.000 0.0000 -1.2202 Cpi Cpv ----------------- -0.4961 -0.4235 -0.3608 -0.4235 0.5151 -0.4235 0.4933 -0.4235 0.4676 -0.4235 0.4446 -0.4236 0.4211 -0.4237 0.3972 -0.4239 0.3727 -0.4241 0.3471 -0.4245 0.3201 -0.4250 0.2915 -0.4257 0.2608 -0.4266 0.2279 -0.4278 0.1924 -0.4292 0.1540 -0.4309 0.1124 -0.4329 0.0672 -0.4354 0.0182 -0.4383 -0.0351 -0.4417 -0.0929 -0.4457 -0.1557 -0.4503 -0.2237 -0.4556 -0.2974 -0.4618 -0.3772 -0.4690 -0.4633 -0.4772 -0.5562 -0.4869 -0.6562 -0.4982 -0.7638 -0.5118 -0.8794 -0.5285 -1.0034 -0.5503 -1.1363 -0.5855 -1.2789 -0.6020 -1.4319 -0.6033 -1.5962 -0.6047 -1.7733 -0.6062 -1.9651 -0.6080 -2.1740 -0.6100 -2.4036 -0.6122 -2.6590 -0.6149 -2.9473 -0.6179 -3.2790 -0.6215 -3.6697 -0.6257 -4.1429 -0.6308 -4.7359 -0.6371 -5.5091 -0.6453 -6.5669 -0.6566 -8.0980 -0.6743 -10.4701 -0.7077 -14.4045 -0.7883 -21.3011 -1.0075 -29.4172 -1.2202 -20.7339 -0.2046 -7.5774 0.7819 -2.2987 0.9949 -0.2876 0.9678 0.5209 0.8742 0.8496 0.7804 0.9716 0.6872 1.0000 0.6098 0.9852 0.5409 0.9515 0.4825 0.9105 0.4323 0.8682 0.3892 0.8276 0.3519 0.7899 0.3193 0.7557 0.2905 0.7249 0.2646 0.6973 0.2408 0.6727 0.2186 0.6507 0.1974 0.6310 0.1767 0.6131 0.1561 0.5969 0.1353 0.5820 0.1139 0.5682 0.0918 0.5553 0.0687 0.5433 0.0445 0.5319 0.0190 0.5211 -0.0078 0.5110 -0.0360 0.5014 -0.0654 0.4924 -0.0960 0.4841 -0.1276 0.4765 -0.1600 0.4698 -0.1928 0.4640 -0.2255 0.4593 -0.2576 0.4559 -0.2883 0.4539 -0.3169 0.4536 -0.3426 0.4554 -0.3647 0.4594 -0.3829 0.4663 -0.3970 0.4763 -0.4073 0.4913 -0.4143 0.5125 -0.4187 0.5383 -0.4213 0.6457 -0.4227 -0.4961 -0.4235 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 22.000 0.322 0.802 -0.115 0.555 1.000 0.0000 -1.2457 Cpi Cpv ----------------- -0.4837 -0.4267 -0.3495 -0.4267 0.5191 -0.4267 0.4974 -0.4267 0.4719 -0.4267 0.4490 -0.4268 0.4256 -0.4269 0.4017 -0.4271 0.3773 -0.4273 0.3516 -0.4277 0.3247 -0.4282 0.2960 -0.4289 0.2653 -0.4298 0.2323 -0.4309 0.1967 -0.4323 0.1582 -0.4340 0.1164 -0.4361 0.0710 -0.4385 0.0217 -0.4414 -0.0319 -0.4448 -0.0901 -0.4488 -0.1533 -0.4534 -0.2219 -0.4587 -0.2962 -0.4648 -0.3767 -0.4719 -0.4636 -0.4801 -0.5575 -0.4896 -0.6587 -0.5008 -0.7676 -0.5141 -0.8848 -0.5300 -1.0106 -0.5501 -1.1456 -0.5776 -1.2905 -0.6267 -1.4462 -0.6279 -1.6138 -0.6293 -1.7945 -0.6309 -1.9906 -0.6327 -2.2044 -0.6347 -2.4399 -0.6370 -2.7022 -0.6396 -2.9988 -0.6427 -3.3406 -0.6463 -3.7437 -0.6505 -4.2327 -0.6556 -4.8462 -0.6619 -5.6473 -0.6698 -6.7446 -0.6806 -8.3351 -0.6971 -10.8033 -0.7273 -14.9063 -0.7994 -22.1225 -1.0040 -30.7074 -1.2457 -21.8146 -0.2723 -8.0867 0.7504 -2.5370 0.9898 -0.4053 0.9760 0.4617 0.8891 0.8213 0.7980 0.9606 0.7061 0.9991 0.6288 0.9904 0.5596 0.9602 0.5005 0.9214 0.4496 0.8803 0.4056 0.8403 0.3674 0.8028 0.3339 0.7685 0.3042 0.7375 0.2774 0.7097 0.2528 0.6847 0.2298 0.6623 0.2079 0.6421 0.1865 0.6238 0.1652 0.6072 0.1437 0.5919 0.1218 0.5777 0.0990 0.5644 0.0754 0.5520 0.0506 0.5403 0.0245 0.5293 -0.0028 0.5188 -0.0315 0.5089 -0.0615 0.4997 -0.0926 0.4911 -0.1248 0.4833 -0.1578 0.4763 -0.1912 0.4703 -0.2245 0.4654 -0.2571 0.4618 -0.2884 0.4596 -0.3176 0.4591 -0.3438 0.4607 -0.3664 0.4645 -0.3851 0.4711 -0.3995 0.4810 -0.4101 0.4957 -0.4172 0.5166 -0.4217 0.5422 -0.4244 0.6487 -0.4259 -0.4837 -0.4267 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 22.500 0.309 0.763 -0.109 0.540 1.000 0.0000 -1.1568 Cpi Cpv ----------------- -0.4710 -0.3898 -0.3381 -0.3898 0.5232 -0.3898 0.5016 -0.3898 0.4762 -0.3898 0.4534 -0.3899 0.4301 -0.3900 0.4063 -0.3901 0.3819 -0.3904 0.3563 -0.3907 0.3293 -0.3912 0.3006 -0.3918 0.2699 -0.3926 0.2368 -0.3936 0.2011 -0.3948 0.1624 -0.3964 0.1204 -0.3982 0.0749 -0.4004 0.0253 -0.4030 -0.0286 -0.4060 -0.0872 -0.4095 -0.1508 -0.4135 -0.2199 -0.4182 -0.2948 -0.4236 -0.3760 -0.4298 -0.4638 -0.4369 -0.5586 -0.4452 -0.6610 -0.4548 -0.7712 -0.4660 -0.8899 -0.4795 -1.0174 -0.4960 -1.1545 -0.5178 -1.3018 -0.5532 -1.4602 -0.5692 -1.6309 -0.5706 -1.8154 -0.5720 -2.0157 -0.5737 -2.2345 -0.5756 -2.4759 -0.5777 -2.7451 -0.5802 -3.0500 -0.5831 -3.4019 -0.5864 -3.8176 -0.5904 -4.3224 -0.5952 -4.9567 -0.6010 -5.7859 -0.6084 -6.9232 -0.6183 -8.5739 -0.6333 -11.1395 -0.6605 -15.4136 -0.7249 -22.9551 -0.9127 -32.0195 -1.1568 -22.9179 -0.2479 -8.6094 0.7486 -2.7830 0.9884 -0.5280 0.9786 0.3991 0.8955 0.7906 0.8069 0.9478 0.7170 0.9968 0.6410 0.9944 0.5726 0.9681 0.5142 0.9316 0.4636 0.8919 0.4199 0.8526 0.3819 0.8154 0.3486 0.7811 0.3189 0.7499 0.2923 0.7218 0.2678 0.6965 0.2450 0.6737 0.2232 0.6531 0.2021 0.6345 0.1811 0.6174 0.1600 0.6017 0.1385 0.5871 0.1163 0.5735 0.0932 0.5608 0.0690 0.5488 0.0437 0.5374 0.0172 0.5266 -0.0105 0.5165 -0.0395 0.5070 -0.0696 0.4982 -0.1006 0.4901 -0.1324 0.4829 -0.1644 0.4766 -0.1964 0.4715 -0.2277 0.4677 -0.2577 0.4653 -0.2855 0.4646 -0.3106 0.4660 -0.3322 0.4696 -0.3499 0.4761 -0.3637 0.4857 -0.3737 0.5002 -0.3806 0.5209 -0.3849 0.5462 -0.3875 0.6517 -0.3890 -0.4710 -0.3898 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 23.000 0.337 0.808 -0.115 0.512 1.000 0.0000 -1.2227 Cpi Cpv ----------------- -0.4583 -0.4107 -0.3265 -0.4107 0.5273 -0.4107 0.5058 -0.4108 0.4807 -0.4108 0.4579 -0.4108 0.4347 -0.4109 0.4110 -0.4111 0.3866 -0.4114 0.3610 -0.4117 0.3341 -0.4122 0.3053 -0.4128 0.2745 -0.4136 0.2414 -0.4147 0.2056 -0.4160 0.1668 -0.4176 0.1247 -0.4195 0.0789 -0.4218 0.0291 -0.4245 -0.0251 -0.4277 -0.0841 -0.4313 -0.1481 -0.4356 -0.2177 -0.4405 -0.2932 -0.4462 -0.3751 -0.4528 -0.4637 -0.4603 -0.5595 -0.4690 -0.6630 -0.4791 -0.7745 -0.4910 -0.8947 -0.5050 -1.0240 -0.5221 -1.1631 -0.5432 -1.3128 -0.5717 -1.4739 -0.6292 -1.6478 -0.6310 -1.8359 -0.6326 -2.0405 -0.6343 -2.2643 -0.6363 -2.5115 -0.6385 -2.7877 -0.6411 -3.1009 -0.6441 -3.4630 -0.6475 -3.8913 -0.6516 -4.4121 -0.6565 -5.0673 -0.6625 -5.9250 -0.6699 -7.1026 -0.6797 -8.8141 -0.6940 -11.4785 -0.7192 -15.9264 -0.7773 -23.7988 -0.9537 -33.3530 -1.2227 -24.0436 -0.3534 -9.1451 0.7013 -3.0367 0.9786 -0.6556 0.9867 0.3333 0.9121 0.7574 0.8266 0.9332 0.7380 0.9931 0.6619 0.9973 0.5927 0.9751 0.5333 0.9411 0.4816 0.9029 0.4366 0.8643 0.3973 0.8275 0.3627 0.7934 0.3318 0.7621 0.3039 0.7337 0.2783 0.7081 0.2543 0.6850 0.2314 0.6641 0.2091 0.6450 0.1871 0.6275 0.1649 0.6115 0.1423 0.5965 0.1190 0.5826 0.0949 0.5695 0.0696 0.5572 0.0432 0.5455 0.0155 0.5345 -0.0134 0.5240 -0.0436 0.5143 -0.0750 0.5052 -0.1073 0.4969 -0.1404 0.4895 -0.1739 0.4830 -0.2073 0.4777 -0.2401 0.4737 -0.2714 0.4711 -0.3007 0.4702 -0.3271 0.4714 -0.3498 0.4748 -0.3686 0.4811 -0.3832 0.4905 -0.3938 0.5047 -0.4010 0.5252 -0.4056 0.5502 -0.4084 0.6547 -0.4099 -0.4583 -0.4107 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 23.500 0.310 0.750 -0.107 0.497 1.000 0.0000 -1.0963 Cpi Cpv ----------------- -0.4453 -0.3638 -0.3147 -0.3638 0.5314 -0.3638 0.5101 -0.3638 0.4851 -0.3638 0.4625 -0.3639 0.4394 -0.3640 0.4158 -0.3641 0.3914 -0.3643 0.3659 -0.3646 0.3389 -0.3651 0.3102 -0.3656 0.2793 -0.3663 0.2461 -0.3672 0.2102 -0.3683 0.1713 -0.3697 0.1290 -0.3713 0.0830 -0.3733 0.0330 -0.3756 -0.0215 -0.3783 -0.0808 -0.3814 -0.1453 -0.3849 -0.2153 -0.3891 -0.2914 -0.3938 -0.3740 -0.3992 -0.4634 -0.4054 -0.5602 -0.4126 -0.6647 -0.4208 -0.7775 -0.4303 -0.8992 -0.4414 -1.0303 -0.4547 -1.1714 -0.4709 -1.3234 -0.4922 -1.4873 -0.5258 -1.6643 -0.5454 -1.8561 -0.5468 -2.0649 -0.5484 -2.2937 -0.5502 -2.5468 -0.5522 -2.8299 -0.5546 -3.1515 -0.5573 -3.5238 -0.5605 -3.9648 -0.5643 -4.5017 -0.5688 -5.1780 -0.5742 -6.0643 -0.5811 -7.2828 -0.5900 -9.0559 -0.6030 -11.8202 -0.6255 -16.4444 -0.6776 -24.6532 -0.8381 -34.7076 -1.0963 -25.1912 -0.2961 -9.6938 0.7108 -3.2980 0.9789 -0.7880 0.9873 0.2641 0.9152 0.7219 0.8320 0.9168 0.7455 0.9880 0.6710 0.9992 0.6031 0.9813 0.5447 0.9499 0.4938 0.9133 0.4494 0.8757 0.4106 0.8393 0.3764 0.8053 0.3460 0.7740 0.3185 0.7454 0.2932 0.7196 0.2697 0.6961 0.2473 0.6748 0.2255 0.6554 0.2040 0.6376 0.1825 0.6212 0.1606 0.6059 0.1382 0.5916 0.1149 0.5782 0.0906 0.5656 0.0653 0.5536 0.0388 0.5423 0.0112 0.5316 -0.0176 0.5216 -0.0474 0.5123 -0.0782 0.5038 -0.1096 0.4961 -0.1413 0.4894 -0.1728 0.4839 -0.2037 0.4797 -0.2332 0.4769 -0.2607 0.4758 -0.2854 0.4768 -0.3067 0.4801 -0.3242 0.4861 -0.3378 0.4953 -0.3477 0.5094 -0.3545 0.5295 -0.3588 0.5542 -0.3615 0.6578 -0.3630 -0.4453 -0.3638 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 24.000 0.341 0.795 -0.113 0.473 1.000 0.0000 -1.1535 Cpi Cpv ----------------- -0.4322 -0.3834 -0.3028 -0.3834 0.5356 -0.3834 0.5145 -0.3834 0.4896 -0.3834 0.4672 -0.3835 0.4441 -0.3835 0.4206 -0.3837 0.3963 -0.3839 0.3708 -0.3842 0.3438 -0.3847 0.3151 -0.3853 0.2842 -0.3860 0.2509 -0.3869 0.2150 -0.3881 0.1759 -0.3895 0.1335 -0.3912 0.0873 -0.3933 0.0370 -0.3957 -0.0177 -0.3985 -0.0773 -0.4018 -0.1422 -0.4056 -0.2128 -0.4100 -0.2894 -0.4151 -0.3727 -0.4209 -0.4629 -0.4275 -0.5606 -0.4352 -0.6662 -0.4440 -0.7803 -0.4542 -0.9034 -0.4662 -1.0362 -0.4804 -1.1794 -0.4976 -1.3337 -0.5191 -1.5003 -0.5480 -1.6804 -0.6071 -1.8758 -0.6088 -2.0889 -0.6104 -2.3227 -0.6123 -2.5816 -0.6144 -2.8718 -0.6169 -3.2018 -0.6197 -3.5844 -0.6230 -4.0380 -0.6269 -4.5912 -0.6316 -5.2888 -0.6372 -6.2040 -0.6441 -7.4637 -0.6531 -9.2990 -0.6657 -12.1646 -0.6869 -16.9676 -0.7343 -25.5181 -0.8837 -36.0828 -1.1535 -26.3604 -0.4008 -10.2553 0.6602 -3.5669 0.9663 -0.9252 0.9934 0.1916 0.9303 0.6840 0.8506 0.8986 0.7658 0.9815 0.6913 1.0000 0.6229 0.9865 0.5637 0.9580 0.5117 0.9231 0.4661 0.8865 0.4262 0.8507 0.3907 0.8169 0.3591 0.7856 0.3304 0.7569 0.3040 0.7308 0.2794 0.7071 0.2559 0.6855 0.2330 0.6657 0.2105 0.6476 0.1880 0.6308 0.1651 0.6152 0.1415 0.6006 0.1172 0.5869 0.0919 0.5740 0.0655 0.5617 0.0379 0.5501 0.0091 0.5392 -0.0208 0.5289 -0.0519 0.5194 -0.0839 0.5106 -0.1166 0.5028 -0.1496 0.4959 -0.1826 0.4902 -0.2149 0.4857 -0.2458 0.4828 -0.2746 0.4815 -0.3006 0.4823 -0.3230 0.4854 -0.3415 0.4912 -0.3559 0.5002 -0.3664 0.5140 -0.3736 0.5339 -0.3782 0.5583 -0.3810 0.6610 -0.3825 -0.4322 -0.3834 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 24.500 0.316 0.747 -0.106 0.463 1.000 0.0000 -1.0395 Cpi Cpv ----------------- -0.4189 -0.3474 -0.2908 -0.3474 0.5399 -0.3474 0.5189 -0.3474 0.4942 -0.3475 0.4719 -0.3475 0.4489 -0.3476 0.4255 -0.3477 0.4012 -0.3479 0.3757 -0.3482 0.3488 -0.3486 0.3200 -0.3491 0.2891 -0.3498 0.2558 -0.3506 0.2198 -0.3516 0.1806 -0.3529 0.1380 -0.3544 0.0917 -0.3562 0.0412 -0.3583 -0.0138 -0.3607 -0.0737 -0.3636 -0.1390 -0.3669 -0.2101 -0.3706 -0.2873 -0.3749 -0.3711 -0.3798 -0.4621 -0.3855 -0.5607 -0.3919 -0.6674 -0.3992 -0.7828 -0.4077 -0.9074 -0.4175 -1.0419 -0.4290 -1.1870 -0.4426 -1.3437 -0.4596 -1.5129 -0.4819 -1.6962 -0.5198 -1.8952 -0.5341 -2.1126 -0.5357 -2.3513 -0.5374 -2.6162 -0.5394 -2.9133 -0.5416 -3.2518 -0.5442 -3.6446 -0.5473 -4.1111 -0.5509 -4.6806 -0.5553 -5.3995 -0.5605 -6.3439 -0.5669 -7.6452 -0.5752 -9.5435 -0.5867 -12.5116 -0.6059 -17.4957 -0.6485 -26.3933 -0.7838 -37.4783 -1.0395 -27.5510 -0.3518 -10.8294 0.6668 -3.8432 0.9659 -1.0672 0.9941 0.1158 0.9336 0.6437 0.8561 0.8786 0.7732 0.9737 0.7001 0.9997 0.6328 0.9910 0.5744 0.9654 0.5229 0.9323 0.4779 0.8968 0.4382 0.8617 0.4031 0.8281 0.3717 0.7969 0.3432 0.7682 0.3171 0.7419 0.2926 0.7179 0.2694 0.6960 0.2469 0.6760 0.2248 0.6575 0.2026 0.6404 0.1802 0.6245 0.1572 0.6096 0.1335 0.5956 0.1089 0.5824 0.0832 0.5698 0.0565 0.5580 0.0286 0.5468 -0.0003 0.5363 -0.0303 0.5265 -0.0611 0.5176 -0.0926 0.5095 -0.1243 0.5024 -0.1559 0.4965 -0.1868 0.4918 -0.2163 0.4887 -0.2438 0.4872 -0.2685 0.4878 -0.2899 0.4907 -0.3074 0.4963 -0.3211 0.5052 -0.3311 0.5187 -0.3379 0.5384 -0.3423 0.5625 -0.3450 0.6641 -0.3466 -0.4189 -0.3474 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 25.000 0.318 0.746 -0.106 0.444 1.000 0.0000 -1.0087 Cpi Cpv ----------------- -0.4055 -0.3398 -0.2786 -0.3398 0.5442 -0.3398 0.5234 -0.3398 0.4989 -0.3398 0.4766 -0.3399 0.4538 -0.3399 0.4304 -0.3401 0.4062 -0.3403 0.3808 -0.3405 0.3539 -0.3409 0.3251 -0.3414 0.2942 -0.3420 0.2608 -0.3428 0.2247 -0.3438 0.1854 -0.3450 0.1427 -0.3465 0.0962 -0.3482 0.0455 -0.3502 -0.0098 -0.3525 -0.0700 -0.3553 -0.1356 -0.3584 -0.2071 -0.3620 -0.2849 -0.3661 -0.3694 -0.3708 -0.4612 -0.3761 -0.5607 -0.3822 -0.6684 -0.3892 -0.7850 -0.3971 -0.9111 -0.4064 -1.0473 -0.4171 -1.1943 -0.4297 -1.3533 -0.4451 -1.5252 -0.4647 -1.7116 -0.4929 -1.9143 -0.5289 -2.1358 -0.5304 -2.3796 -0.5321 -2.6503 -0.5340 -2.9545 -0.5363 -3.3014 -0.5388 -3.7045 -0.5419 -4.1839 -0.5454 -4.7698 -0.5497 -5.5103 -0.5548 -6.4840 -0.5611 -7.8273 -0.5691 -9.7892 -0.5801 -12.8609 -0.5979 -18.0286 -0.6366 -27.2784 -0.7600 -38.8936 -1.0087 -28.7624 -0.3788 -11.4159 0.6437 -4.1268 0.9581 -1.2139 0.9965 0.0368 0.9419 0.6011 0.8674 0.8568 0.7865 0.9645 0.7142 0.9983 0.6473 0.9945 0.5888 0.9720 0.5372 0.9410 0.4919 0.9067 0.4518 0.8722 0.4162 0.8391 0.3844 0.8080 0.3554 0.7792 0.3288 0.7528 0.3040 0.7286 0.2803 0.7064 0.2575 0.6861 0.2350 0.6673 0.2125 0.6499 0.1898 0.6337 0.1665 0.6185 0.1426 0.6042 0.1178 0.5907 0.0920 0.5779 0.0651 0.5658 0.0371 0.5544 0.0081 0.5437 -0.0220 0.5337 -0.0529 0.5245 -0.0844 0.5162 -0.1162 0.5089 -0.1478 0.5028 -0.1787 0.4980 -0.2083 0.4946 -0.2358 0.4930 -0.2606 0.4934 -0.2819 0.4961 -0.2995 0.5015 -0.3132 0.5101 -0.3233 0.5235 -0.3301 0.5428 -0.3346 0.5667 -0.3373 0.6673 -0.3389 -0.4055 -0.3398 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 25.500 0.338 0.769 -0.110 0.431 1.000 0.0000 -1.0187 Cpi Cpv ----------------- -0.3920 -0.3474 -0.2663 -0.3474 0.5486 -0.3474 0.5279 -0.3474 0.5035 -0.3474 0.4814 -0.3475 0.4587 -0.3476 0.4354 -0.3477 0.4113 -0.3479 0.3859 -0.3482 0.3590 -0.3485 0.3303 -0.3490 0.2993 -0.3497 0.2659 -0.3505 0.2297 -0.3515 0.1904 -0.3527 0.1476 -0.3541 0.1009 -0.3559 0.0500 -0.3579 -0.0055 -0.3604 -0.0661 -0.3632 -0.1321 -0.3664 -0.2040 -0.3701 -0.2823 -0.3743 -0.3675 -0.3792 -0.4600 -0.3847 -0.5604 -0.3910 -0.6692 -0.3982 -0.7870 -0.4065 -0.9145 -0.4161 -1.0523 -0.4273 -1.2014 -0.4406 -1.3626 -0.4566 -1.5372 -0.4765 -1.7266 -0.5033 -1.9329 -0.5578 -2.1587 -0.5613 -2.4074 -0.5630 -2.6840 -0.5650 -2.9952 -0.5673 -3.3506 -0.5699 -3.7641 -0.5729 -4.2564 -0.5765 -4.8588 -0.5808 -5.6210 -0.5860 -6.6243 -0.5923 -8.0099 -0.6003 -10.0360 -0.6110 -13.2126 -0.6279 -18.5661 -0.6635 -28.1733 -0.7762 -40.3282 -1.0187 -29.9944 -0.4452 -12.0147 0.6035 -4.4177 0.9452 -1.3653 0.9988 -0.0455 0.9523 0.5561 0.8812 0.8333 0.8025 0.9540 0.7307 0.9958 0.6639 0.9972 0.6051 0.9780 0.5530 0.9491 0.5069 0.9161 0.4661 0.8824 0.4297 0.8497 0.3970 0.8187 0.3673 0.7900 0.3399 0.7634 0.3143 0.7391 0.2899 0.7167 0.2663 0.6961 0.2431 0.6770 0.2199 0.6593 0.1965 0.6429 0.1726 0.6274 0.1480 0.6128 0.1225 0.5991 0.0960 0.5860 0.0684 0.5737 0.0398 0.5620 0.0100 0.5511 -0.0208 0.5409 -0.0524 0.5315 -0.0847 0.5230 -0.1172 0.5155 -0.1496 0.5092 -0.1814 0.5042 -0.2118 0.5006 -0.2401 0.4988 -0.2656 0.4990 -0.2876 0.5015 -0.3058 0.5068 -0.3199 0.5152 -0.3303 0.5283 -0.3374 0.5474 -0.3420 0.5709 -0.3449 0.6706 -0.3465 -0.3920 -0.3474 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 26.000 0.321 0.740 -0.107 0.421 1.000 0.0000 -0.9370 Cpi Cpv ----------------- -0.3782 -0.3273 -0.2538 -0.3273 0.5530 -0.3273 0.5325 -0.3274 0.5083 -0.3274 0.4863 -0.3274 0.4637 -0.3275 0.4405 -0.3276 0.4165 -0.3278 0.3911 -0.3280 0.3642 -0.3284 0.3355 -0.3288 0.3045 -0.3294 0.2711 -0.3302 0.2349 -0.3311 0.1954 -0.3322 0.1525 -0.3336 0.1057 -0.3352 0.0546 -0.3370 -0.0012 -0.3392 -0.0620 -0.3417 -0.1284 -0.3446 -0.2008 -0.3480 -0.2796 -0.3517 -0.3653 -0.3560 -0.4586 -0.3609 -0.5598 -0.3665 -0.6696 -0.3728 -0.7887 -0.3801 -0.9176 -0.3884 -1.0571 -0.3980 -1.2080 -0.4092 -1.3715 -0.4226 -1.5487 -0.4391 -1.7413 -0.4608 -1.9512 -0.4974 -2.1812 -0.5132 -2.4349 -0.5148 -2.7174 -0.5166 -3.0356 -0.5188 -3.3994 -0.5212 -3.8233 -0.5241 -4.3286 -0.5275 -4.9476 -0.5316 -5.7316 -0.5365 -6.7648 -0.5425 -8.1931 -0.5500 -10.2840 -0.5601 -13.5665 -0.5757 -19.1081 -0.6079 -29.0775 -0.7096 -41.7818 -0.9370 -31.2465 -0.4218 -12.6255 0.5995 -4.7158 0.9416 -1.5213 0.9993 -0.1309 0.9565 0.5088 0.8877 0.8080 0.8111 0.9420 0.7403 0.9922 0.6744 0.9990 0.6161 0.9833 0.5642 0.9565 0.5183 0.9250 0.4775 0.8922 0.4412 0.8599 0.4084 0.8292 0.3786 0.8005 0.3511 0.7739 0.3254 0.7494 0.3010 0.7268 0.2774 0.7059 0.2542 0.6866 0.2311 0.6687 0.2077 0.6519 0.1840 0.6362 0.1595 0.6214 0.1343 0.6074 0.1080 0.5941 0.0808 0.5815 0.0525 0.5696 0.0232 0.5585 -0.0071 0.5480 -0.0382 0.5384 -0.0699 0.5298 -0.1019 0.5221 -0.1337 0.5156 -0.1648 0.5104 -0.1946 0.5067 -0.2223 0.5047 -0.2472 0.5047 -0.2687 0.5070 -0.2865 0.5121 -0.3003 0.5203 -0.3104 0.5331 -0.3174 0.5520 -0.3220 0.5752 -0.3248 0.6738 -0.3264 -0.3782 -0.3273 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 26.500 0.323 0.740 -0.107 0.404 1.000 0.0000 -0.9090 Cpi Cpv ----------------- -0.3644 -0.3220 -0.2413 -0.3220 0.5574 -0.3220 0.5371 -0.3220 0.5131 -0.3220 0.4913 -0.3221 0.4688 -0.3221 0.4456 -0.3223 0.4217 -0.3224 0.3964 -0.3227 0.3695 -0.3230 0.3408 -0.3235 0.3099 -0.3240 0.2764 -0.3247 0.2401 -0.3256 0.2006 -0.3267 0.1575 -0.3280 0.1106 -0.3296 0.0593 -0.3314 0.0033 -0.3335 -0.0578 -0.3359 -0.1245 -0.3387 -0.1973 -0.3419 -0.2766 -0.3455 -0.3630 -0.3497 -0.4569 -0.3544 -0.5590 -0.3597 -0.6699 -0.3657 -0.7901 -0.3727 -0.9204 -0.3806 -1.0615 -0.3897 -1.2144 -0.4002 -1.3801 -0.4127 -1.5600 -0.4279 -1.7556 -0.4473 -1.9691 -0.4754 -2.2033 -0.5104 -2.4619 -0.5120 -2.7503 -0.5138 -3.0755 -0.5159 -3.4478 -0.5184 -3.8822 -0.5212 -4.4005 -0.5246 -5.0361 -0.5286 -5.8421 -0.5334 -6.9053 -0.5392 -8.3767 -0.5466 -10.5329 -0.5563 -13.9225 -0.5710 -19.6544 -0.6006 -29.9909 -0.6929 -43.2539 -0.9090 -32.5185 -0.4493 -13.2482 0.5736 -5.0209 0.9315 -1.6820 0.9999 -0.2196 0.9635 0.4591 0.8976 0.7810 0.8236 0.9287 0.7533 0.9876 0.6882 0.9999 0.6299 0.9878 0.5779 0.9634 0.5317 0.9334 0.4906 0.9016 0.4538 0.8699 0.4206 0.8394 0.3903 0.8108 0.3624 0.7842 0.3363 0.7595 0.3114 0.7367 0.2874 0.7157 0.2638 0.6962 0.2403 0.6780 0.2167 0.6610 0.1926 0.6450 0.1679 0.6299 0.1424 0.6156 0.1159 0.6021 0.0885 0.5893 0.0600 0.5772 0.0305 0.5658 0.0000 0.5552 -0.0313 0.5454 -0.0631 0.5366 -0.0952 0.5287 -0.1272 0.5220 -0.1584 0.5166 -0.1883 0.5128 -0.2162 0.5106 -0.2412 0.5104 -0.2629 0.5126 -0.2807 0.5174 -0.2946 0.5254 -0.3049 0.5380 -0.3119 0.5566 -0.3165 0.5796 -0.3194 0.6771 -0.3211 -0.3644 -0.3220 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 27.000 0.348 0.768 -0.111 0.392 1.000 0.0000 -0.9317 Cpi Cpv ----------------- -0.3504 -0.3318 -0.2286 -0.3318 0.5619 -0.3318 0.5418 -0.3318 0.5179 -0.3318 0.4962 -0.3319 0.4739 -0.3319 0.4508 -0.3321 0.4269 -0.3322 0.4017 -0.3325 0.3749 -0.3328 0.3462 -0.3333 0.3152 -0.3339 0.2818 -0.3346 0.2454 -0.3355 0.2059 -0.3366 0.1627 -0.3379 0.1156 -0.3395 0.0642 -0.3414 0.0080 -0.3435 -0.0534 -0.3460 -0.1205 -0.3490 -0.1937 -0.3523 -0.2735 -0.3561 -0.3604 -0.3605 -0.4551 -0.3655 -0.5580 -0.3711 -0.6698 -0.3776 -0.7912 -0.3849 -0.9229 -0.3934 -1.0657 -0.4032 -1.2204 -0.4146 -1.3884 -0.4281 -1.5708 -0.4445 -1.7695 -0.4650 -1.9865 -0.4926 -2.2249 -0.5500 -2.4885 -0.5526 -2.7827 -0.5545 -3.1150 -0.5566 -3.4959 -0.5591 -3.9407 -0.5620 -4.4720 -0.5654 -5.1244 -0.5695 -5.9525 -0.5743 -7.0459 -0.5803 -8.5606 -0.5876 -10.7828 -0.5972 -14.2805 -0.6114 -20.2048 -0.6389 -30.9132 -0.7231 -44.7440 -0.9317 -33.8098 -0.5179 -13.8827 0.5176 -5.3331 0.9189 -1.8471 0.9996 -0.3114 0.9734 0.4072 0.9089 0.7522 0.8398 0.9141 0.7686 0.9818 0.7049 0.9999 0.6460 0.9916 0.5936 0.9698 0.5468 0.9414 0.5049 0.9105 0.4674 0.8794 0.4334 0.8493 0.4023 0.8209 0.3736 0.7942 0.3466 0.7695 0.3210 0.7466 0.2962 0.7253 0.2718 0.7056 0.2476 0.6872 0.2232 0.6699 0.1984 0.6537 0.1730 0.6384 0.1467 0.6239 0.1195 0.6102 0.0913 0.5971 0.0620 0.5848 0.0317 0.5732 0.0004 0.5624 -0.0317 0.5524 -0.0644 0.5434 -0.0974 0.5353 -0.1303 0.5285 -0.1625 0.5229 -0.1933 0.5189 -0.2220 0.5165 -0.2480 0.5162 -0.2704 0.5181 -0.2889 0.5228 -0.3034 0.5306 -0.3140 0.5430 -0.3214 0.5613 -0.3261 0.5840 -0.3291 0.6805 -0.3308 -0.3504 -0.3318 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 27.500 0.331 0.741 -0.109 0.385 1.000 0.0000 -0.8545 Cpi Cpv ----------------- -0.3363 -0.3145 -0.2157 -0.3145 0.5665 -0.3145 0.5465 -0.3145 0.5228 -0.3145 0.5013 -0.3145 0.4790 -0.3146 0.4561 -0.3147 0.4323 -0.3149 0.4071 -0.3151 0.3804 -0.3154 0.3517 -0.3159 0.3207 -0.3164 0.2872 -0.3171 0.2509 -0.3179 0.2112 -0.3190 0.1680 -0.3202 0.1208 -0.3216 0.0691 -0.3234 0.0127 -0.3253 -0.0489 -0.3276 -0.1163 -0.3303 -0.1899 -0.3333 -0.2701 -0.3367 -0.3577 -0.3406 -0.4530 -0.3450 -0.5568 -0.3500 -0.6696 -0.3557 -0.7921 -0.3622 -0.9251 -0.3695 -1.0695 -0.3780 -1.2261 -0.3877 -1.3963 -0.3992 -1.5813 -0.4128 -1.7830 -0.4297 -2.0036 -0.4523 -2.2462 -0.4931 -2.5147 -0.5045 -2.8148 -0.5063 -3.1541 -0.5083 -3.5434 -0.5106 -3.9987 -0.5134 -4.5432 -0.5166 -5.2124 -0.5204 -6.0626 -0.5251 -7.1865 -0.5307 -8.7448 -0.5376 -11.0336 -0.5466 -14.6404 -0.5597 -20.7592 -0.5848 -31.8441 -0.6606 -46.2518 -0.8545 -35.1202 -0.4921 -14.5286 0.5134 -5.6522 0.9147 -2.0168 0.9992 -0.4063 0.9764 0.3530 0.9147 0.7216 0.8474 0.8980 0.7774 0.9750 0.7146 0.9991 0.6563 0.9947 0.6042 0.9755 0.5575 0.9488 0.5157 0.9191 0.4781 0.8887 0.4441 0.8590 0.4129 0.8307 0.3841 0.8041 0.3571 0.7793 0.3314 0.7562 0.3065 0.7348 0.2822 0.7149 0.2580 0.6963 0.2336 0.6788 0.2089 0.6624 0.1835 0.6468 0.1574 0.6321 0.1304 0.6182 0.1025 0.6049 0.0735 0.5924 0.0435 0.5806 0.0126 0.5696 -0.0191 0.5595 -0.0514 0.5502 -0.0839 0.5420 -0.1163 0.5349 -0.1480 0.5292 -0.1783 0.5250 -0.2065 0.5225 -0.2320 0.5220 -0.2540 0.5237 -0.2722 0.5282 -0.2864 0.5358 -0.2969 0.5480 -0.3041 0.5660 -0.3088 0.5884 -0.3118 0.6838 -0.3135 -0.3363 -0.3145 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 28.000 0.329 0.735 -0.109 0.371 1.000 0.0000 -0.8194 Cpi Cpv ----------------- -0.3220 -0.3084 -0.2028 -0.3084 0.5711 -0.3084 0.5512 -0.3084 0.5278 -0.3084 0.5064 -0.3084 0.4842 -0.3085 0.4614 -0.3086 0.4377 -0.3088 0.4126 -0.3090 0.3859 -0.3093 0.3572 -0.3097 0.3263 -0.3102 0.2928 -0.3109 0.2564 -0.3117 0.2167 -0.3127 0.1734 -0.3139 0.1260 -0.3153 0.0743 -0.3169 0.0176 -0.3188 -0.0442 -0.3210 -0.1119 -0.3235 -0.1859 -0.3264 -0.2666 -0.3297 -0.3547 -0.3334 -0.4507 -0.3376 -0.5553 -0.3424 -0.6690 -0.3477 -0.7927 -0.3538 -0.9271 -0.3607 -1.0730 -0.3686 -1.2315 -0.3777 -1.4038 -0.3882 -1.5914 -0.4007 -1.7961 -0.4160 -2.0202 -0.4358 -2.2670 -0.4662 -2.5404 -0.4921 -2.8464 -0.4938 -3.1927 -0.4958 -3.5906 -0.4981 -4.0564 -0.5007 -4.6140 -0.5039 -5.3000 -0.5076 -6.1726 -0.5121 -7.3270 -0.5176 -8.9294 -0.5243 -11.2852 -0.5329 -15.0020 -0.5453 -21.3173 -0.5684 -32.7833 -0.6372 -47.7766 -0.8194 -36.4491 -0.5065 -15.1858 0.4909 -5.9780 0.9046 -2.1909 0.9979 -0.5043 0.9808 0.2965 0.9227 0.6894 0.8574 0.8807 0.7888 0.9671 0.7266 0.9974 0.6686 0.9971 0.6166 0.9806 0.5698 0.9557 0.5277 0.9272 0.4898 0.8975 0.4554 0.8683 0.4239 0.8402 0.3948 0.8137 0.3674 0.7889 0.3413 0.7658 0.3161 0.7442 0.2914 0.7241 0.2669 0.7053 0.2423 0.6876 0.2173 0.6710 0.1918 0.6552 0.1655 0.6403 0.1383 0.6261 0.1101 0.6127 0.0810 0.6000 0.0509 0.5880 0.0198 0.5769 -0.0120 0.5665 -0.0444 0.5571 -0.0770 0.5487 -0.1094 0.5415 -0.1412 0.5356 -0.1716 0.5312 -0.1999 0.5285 -0.2254 0.5278 -0.2475 0.5294 -0.2658 0.5337 -0.2801 0.5411 -0.2906 0.5530 -0.2979 0.5707 -0.3026 0.5928 -0.3056 0.6872 -0.3074 -0.3220 -0.3084 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 28.500 0.339 0.746 -0.111 0.357 1.000 0.0000 -0.8180 Cpi Cpv ----------------- -0.3076 -0.3083 -0.1897 -0.3083 0.5757 -0.3083 0.5560 -0.3083 0.5328 -0.3083 0.5115 -0.3084 0.4895 -0.3084 0.4668 -0.3085 0.4431 -0.3087 0.4181 -0.3089 0.3915 -0.3092 0.3628 -0.3096 0.3319 -0.3101 0.2984 -0.3107 0.2620 -0.3115 0.2222 -0.3125 0.1788 -0.3137 0.1314 -0.3151 0.0795 -0.3167 0.0227 -0.3186 -0.0394 -0.3208 -0.1074 -0.3233 -0.1817 -0.3262 -0.2629 -0.3294 -0.3515 -0.3331 -0.4482 -0.3373 -0.5535 -0.3420 -0.6682 -0.3473 -0.7930 -0.3534 -0.9287 -0.3603 -1.0762 -0.3682 -1.2366 -0.3772 -1.4110 -0.3878 -1.6012 -0.4002 -1.8088 -0.4153 -2.0365 -0.4344 -2.2873 -0.4610 -2.5657 -0.5082 -2.8775 -0.5099 -3.2309 -0.5119 -3.6373 -0.5141 -4.1135 -0.5168 -4.6843 -0.5199 -5.3873 -0.5237 -6.2823 -0.5282 -7.4675 -0.5336 -9.1141 -0.5402 -11.5375 -0.5486 -15.3654 -0.5604 -21.8792 -0.5819 -33.7305 -0.6448 -49.3181 -0.8180 -37.7963 -0.5538 -15.8541 0.4522 -6.3106 0.8886 -2.3693 0.9953 -0.6054 0.9859 0.2377 0.9324 0.6554 0.8695 0.8620 0.8022 0.9582 0.7407 0.9948 0.6828 0.9988 0.6306 0.9851 0.5836 0.9622 0.5411 0.9349 0.5028 0.9061 0.4678 0.8773 0.4358 0.8495 0.4061 0.8231 0.3782 0.7983 0.3516 0.7751 0.3259 0.7535 0.3007 0.7332 0.2757 0.7142 0.2506 0.6963 0.2252 0.6795 0.1992 0.6636 0.1725 0.6484 0.1449 0.6341 0.1163 0.6205 0.0868 0.6076 0.0563 0.5954 0.0248 0.5841 -0.0074 0.5735 -0.0402 0.5640 -0.0732 0.5554 -0.1061 0.5480 -0.1383 0.5420 -0.1691 0.5374 -0.1979 0.5345 -0.2238 0.5337 -0.2463 0.5351 -0.2649 0.5392 -0.2794 0.5464 -0.2901 0.5581 -0.2975 0.5755 -0.3024 0.5973 -0.3055 0.6906 -0.3073 -0.3076 -0.3083 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 29.000 0.349 0.752 -0.113 0.351 1.000 0.0000 -0.8076 Cpi Cpv ----------------- -0.2931 -0.3088 -0.1766 -0.3088 0.5804 -0.3088 0.5609 -0.3088 0.5378 -0.3089 0.5167 -0.3089 0.4948 -0.3090 0.4722 -0.3091 0.4487 -0.3092 0.4237 -0.3094 0.3971 -0.3097 0.3685 -0.3101 0.3376 -0.3106 0.3041 -0.3113 0.2677 -0.3121 0.2279 -0.3130 0.1844 -0.3142 0.1369 -0.3155 0.0849 -0.3171 0.0279 -0.3190 -0.0345 -0.3212 -0.1027 -0.3237 -0.1774 -0.3265 -0.2590 -0.3298 -0.3482 -0.3335 -0.4455 -0.3376 -0.5516 -0.3424 -0.6672 -0.3477 -0.7931 -0.3538 -0.9300 -0.3607 -1.0791 -0.3686 -1.2413 -0.3777 -1.4179 -0.3883 -1.6105 -0.4008 -1.8212 -0.4159 -2.0523 -0.4347 -2.3073 -0.4601 -2.5905 -0.5123 -2.9082 -0.5170 -3.2685 -0.5189 -3.6835 -0.5212 -4.1703 -0.5238 -4.7543 -0.5269 -5.4742 -0.5306 -6.3917 -0.5350 -7.6078 -0.5404 -9.2990 -0.5469 -11.7904 -0.5550 -15.7303 -0.5663 -22.4444 -0.5862 -34.6854 -0.6437 -50.8759 -0.8076 -39.1613 -0.5907 -16.5334 0.4175 -6.6498 0.8731 -2.5521 0.9920 -0.7095 0.9899 0.1768 0.9408 0.6197 0.8803 0.8419 0.8144 0.9481 0.7535 0.9913 0.6958 0.9998 0.6437 0.9890 0.5964 0.9681 0.5536 0.9422 0.5148 0.9142 0.4795 0.8860 0.4469 0.8586 0.4167 0.8324 0.3883 0.8076 0.3612 0.7844 0.3350 0.7626 0.3094 0.7422 0.2839 0.7230 0.2584 0.7050 0.2325 0.6880 0.2061 0.6718 0.1790 0.6565 0.1510 0.6420 0.1220 0.6282 0.0921 0.6152 0.0611 0.6028 0.0293 0.5913 -0.0033 0.5806 -0.0366 0.5708 -0.0700 0.5621 -0.1034 0.5546 -0.1360 0.5484 -0.1672 0.5436 -0.1964 0.5406 -0.2228 0.5396 -0.2456 0.5408 -0.2645 0.5447 -0.2793 0.5517 -0.2903 0.5632 -0.2978 0.5804 -0.3028 0.6019 -0.3060 0.6941 -0.3078 -0.2931 -0.3088 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 29.500 0.338 0.737 -0.112 0.343 1.000 0.0000 -0.7557 Cpi Cpv ----------------- -0.2785 -0.2995 -0.1633 -0.2995 0.5851 -0.2995 0.5657 -0.2995 0.5429 -0.2996 0.5219 -0.2996 0.5002 -0.2997 0.4777 -0.2998 0.4542 -0.2999 0.4293 -0.3001 0.4028 -0.3004 0.3743 -0.3008 0.3434 -0.3013 0.3099 -0.3019 0.2735 -0.3026 0.2337 -0.3036 0.1901 -0.3047 0.1425 -0.3060 0.0904 -0.3075 0.0332 -0.3092 -0.0294 -0.3113 -0.0979 -0.3136 -0.1729 -0.3163 -0.2549 -0.3193 -0.3446 -0.3227 -0.4425 -0.3266 -0.5494 -0.3309 -0.6659 -0.3358 -0.7928 -0.3414 -0.9311 -0.3476 -1.0817 -0.3548 -1.2456 -0.3629 -1.4244 -0.3723 -1.6195 -0.3833 -1.8331 -0.3964 -2.0677 -0.4126 -2.3268 -0.4341 -2.6149 -0.4721 -2.9384 -0.4858 -3.3057 -0.4877 -3.7292 -0.4898 -4.2265 -0.4924 -4.8237 -0.4953 -5.5607 -0.4989 -6.5008 -0.5031 -7.7480 -0.5082 -9.4839 -0.5144 -12.0438 -0.5221 -16.0966 -0.5327 -23.0130 -0.5509 -35.6478 -0.6028 -52.4493 -0.7557 -40.5436 -0.5821 -17.2233 0.4042 -6.9954 0.8645 -2.7392 0.9896 -0.8166 0.9922 0.1136 0.9464 0.5824 0.8879 0.8205 0.8234 0.9370 0.7634 0.9870 0.7062 1.0000 0.6543 0.9924 0.6071 0.9736 0.5643 0.9490 0.5254 0.9220 0.4898 0.8945 0.4571 0.8674 0.4267 0.8413 0.3980 0.8167 0.3707 0.7934 0.3443 0.7716 0.3185 0.7510 0.2929 0.7318 0.2672 0.7136 0.2412 0.6964 0.2147 0.6801 0.1874 0.6646 0.1594 0.6499 0.1304 0.6359 0.1004 0.6227 0.0695 0.6102 0.0377 0.5985 0.0051 0.5876 -0.0280 0.5777 -0.0614 0.5689 -0.0946 0.5611 -0.1271 0.5548 -0.1583 0.5499 -0.1873 0.5467 -0.2136 0.5455 -0.2364 0.5466 -0.2552 0.5503 -0.2700 0.5571 -0.2809 0.5683 -0.2885 0.5852 -0.2935 0.6064 -0.2966 0.6976 -0.2985 -0.2785 -0.2995 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 30.000 0.338 0.734 -0.113 0.331 1.000 0.0000 -0.7319 Cpi Cpv ----------------- -0.2638 -0.2958 -0.1500 -0.2958 0.5898 -0.2958 0.5707 -0.2958 0.5480 -0.2959 0.5272 -0.2959 0.5056 -0.2959 0.4832 -0.2960 0.4599 -0.2962 0.4350 -0.2964 0.4086 -0.2967 0.3801 -0.2970 0.3493 -0.2975 0.3158 -0.2981 0.2794 -0.2988 0.2395 -0.2997 0.1959 -0.3008 0.1482 -0.3021 0.0960 -0.3035 0.0387 -0.3052 -0.0241 -0.3072 -0.0929 -0.3095 -0.1682 -0.3121 -0.2506 -0.3150 -0.3408 -0.3183 -0.4393 -0.3220 -0.5469 -0.3262 -0.6643 -0.3309 -0.7923 -0.3362 -0.9319 -0.3422 -1.0839 -0.3490 -1.2497 -0.3567 -1.4305 -0.3656 -1.6281 -0.3759 -1.8446 -0.3881 -2.0826 -0.4031 -2.3458 -0.4224 -2.6388 -0.4521 -2.9681 -0.4786 -3.3424 -0.4804 -3.7744 -0.4825 -4.2823 -0.4850 -4.8927 -0.4879 -5.6468 -0.4914 -6.6096 -0.4955 -7.8879 -0.5005 -9.6689 -0.5065 -12.2978 -0.5139 -16.4643 -0.5239 -23.5846 -0.5407 -36.6173 -0.5880 -54.0380 -0.7319 -41.9429 -0.6004 -17.9237 0.3770 -7.3475 0.8506 -2.9305 0.9856 -0.9267 0.9947 0.0482 0.9531 0.5433 0.8969 0.7978 0.8340 0.9248 0.7747 0.9818 0.7179 0.9995 0.6662 0.9951 0.6189 0.9785 0.5759 0.9555 0.5368 0.9295 0.5009 0.9026 0.4678 0.8759 0.4370 0.8501 0.4080 0.8255 0.3803 0.8023 0.3536 0.7804 0.3274 0.7598 0.3015 0.7404 0.2755 0.7221 0.2492 0.7047 0.2223 0.6883 0.1948 0.6726 0.1665 0.6578 0.1373 0.6436 0.1071 0.6302 0.0760 0.6176 0.0439 0.6057 0.0112 0.5947 -0.0222 0.5846 -0.0558 0.5756 -0.0892 0.5677 -0.1219 0.5612 -0.1533 0.5562 -0.1826 0.5528 -0.2090 0.5515 -0.2320 0.5524 -0.2510 0.5559 -0.2659 0.5625 -0.2769 0.5735 -0.2846 0.5901 -0.2897 0.6110 -0.2929 0.7011 -0.2948 -0.2638 -0.2958 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 30.500 0.346 0.742 -0.115 0.318 1.000 0.0000 -0.7322 Cpi Cpv ----------------- -0.2490 -0.2952 -0.1365 -0.2952 0.5946 -0.2952 0.5756 -0.2952 0.5531 -0.2952 0.5325 -0.2952 0.5110 -0.2953 0.4888 -0.2954 0.4655 -0.2955 0.4408 -0.2957 0.4144 -0.2960 0.3860 -0.2963 0.3552 -0.2968 0.3218 -0.2974 0.2853 -0.2981 0.2455 -0.2990 0.2018 -0.3000 0.1541 -0.3013 0.1017 -0.3027 0.0443 -0.3044 -0.0187 -0.3064 -0.0877 -0.3086 -0.1634 -0.3112 -0.2462 -0.3140 -0.3368 -0.3173 -0.4360 -0.3210 -0.5443 -0.3251 -0.6625 -0.3298 -0.7916 -0.3351 -0.9323 -0.3410 -1.0859 -0.3478 -1.2533 -0.3555 -1.4362 -0.3643 -1.6363 -0.3746 -1.8557 -0.3867 -2.0972 -0.4014 -2.3644 -0.4200 -2.6622 -0.4462 -2.9973 -0.4920 -3.3786 -0.4938 -3.8191 -0.4959 -4.3375 -0.4983 -4.9613 -0.5012 -5.7324 -0.5047 -6.7179 -0.5088 -8.0276 -0.5137 -9.8539 -0.5196 -12.5521 -0.5269 -16.8332 -0.5364 -24.1592 -0.5521 -37.5937 -0.5954 -55.6415 -0.7322 -43.3587 -0.6420 -18.6344 0.3370 -7.7059 0.8314 -3.1259 0.9799 -1.0397 0.9971 -0.0194 0.9604 0.5026 0.9069 0.7738 0.8458 0.9116 0.7873 0.9757 0.7309 0.9983 0.6793 0.9972 0.6319 0.9829 0.5886 0.9615 0.5491 0.9366 0.5128 0.9104 0.4793 0.8841 0.4481 0.8586 0.4186 0.8342 0.3905 0.8110 0.3633 0.7891 0.3366 0.7684 0.3103 0.7489 0.2838 0.7305 0.2571 0.7130 0.2299 0.6964 0.2020 0.6806 0.1733 0.6656 0.1437 0.6513 0.1132 0.6377 0.0816 0.6249 0.0492 0.6129 0.0161 0.6018 -0.0177 0.5916 -0.0516 0.5824 -0.0855 0.5744 -0.1186 0.5677 -0.1504 0.5625 -0.1800 0.5590 -0.2069 0.5575 -0.2302 0.5582 -0.2495 0.5616 -0.2647 0.5679 -0.2759 0.5787 -0.2837 0.5951 -0.2889 0.6156 -0.2921 0.7046 -0.2941 -0.2490 -0.2952 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 31.000 0.358 0.750 -0.117 0.312 1.000 0.0000 -0.7317 Cpi Cpv ----------------- -0.2341 -0.2966 -0.1229 -0.2966 0.5994 -0.2966 0.5806 -0.2966 0.5583 -0.2966 0.5378 -0.2966 0.5165 -0.2967 0.4944 -0.2968 0.4713 -0.2969 0.4466 -0.2971 0.4203 -0.2974 0.3920 -0.2977 0.3612 -0.2982 0.3278 -0.2988 0.2914 -0.2995 0.2515 -0.3004 0.2078 -0.3014 0.1600 -0.3026 0.1075 -0.3041 0.0500 -0.3057 -0.0132 -0.3077 -0.0824 -0.3099 -0.1584 -0.3124 -0.2416 -0.3153 -0.3327 -0.3186 -0.4324 -0.3224 -0.5414 -0.3265 -0.6605 -0.3313 -0.7905 -0.3366 -0.9325 -0.3426 -1.0875 -0.3495 -1.2567 -0.3573 -1.4416 -0.3663 -1.6441 -0.3768 -1.8664 -0.3893 -2.1113 -0.4042 -2.3825 -0.4229 -2.6852 -0.4483 -3.0260 -0.5014 -3.4143 -0.5058 -3.8633 -0.5079 -4.3922 -0.5103 -5.0292 -0.5132 -5.8176 -0.5166 -6.8259 -0.5207 -8.1670 -0.5255 -10.0388 -0.5314 -12.8068 -0.5384 -17.2032 -0.5476 -24.7366 -0.5622 -38.5766 -0.6018 -57.2592 -0.7317 -44.7906 -0.6809 -19.3552 0.2969 -8.0704 0.8114 -3.3255 0.9732 -1.1556 0.9988 -0.0891 0.9671 0.4602 0.9163 0.7484 0.8570 0.8973 0.7993 0.9688 0.7434 0.9964 0.6919 0.9988 0.6444 0.9868 0.6009 0.9670 0.5610 0.9433 0.5243 0.9178 0.4904 0.8921 0.4586 0.8669 0.4287 0.8427 0.4001 0.8196 0.3724 0.7977 0.3453 0.7769 0.3185 0.7573 0.2916 0.7388 0.2645 0.7212 0.2368 0.7044 0.2085 0.6885 0.1793 0.6734 0.1493 0.6589 0.1183 0.6452 0.0864 0.6323 0.0535 0.6201 0.0199 0.6088 -0.0143 0.5985 -0.0488 0.5891 -0.0831 0.5810 -0.1167 0.5742 -0.1490 0.5688 -0.1792 0.5652 -0.2065 0.5635 -0.2302 0.5641 -0.2499 0.5672 -0.2654 0.5734 -0.2769 0.5840 -0.2848 0.6000 -0.2901 0.6203 -0.2935 0.7082 -0.2955 -0.2341 -0.2966 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 31.500 0.347 0.736 -0.117 0.305 1.000 0.0000 -0.6853 Cpi Cpv ----------------- -0.2190 -0.2891 -0.1093 -0.2891 0.6042 -0.2891 0.5856 -0.2891 0.5636 -0.2891 0.5432 -0.2892 0.5221 -0.2892 0.5001 -0.2893 0.4770 -0.2894 0.4525 -0.2896 0.4263 -0.2899 0.3980 -0.2902 0.3673 -0.2907 0.3339 -0.2912 0.2975 -0.2919 0.2576 -0.2928 0.2139 -0.2938 0.1661 -0.2949 0.1135 -0.2963 0.0558 -0.2979 -0.0075 -0.2998 -0.0770 -0.3019 -0.1532 -0.3043 -0.2368 -0.3070 -0.3283 -0.3101 -0.4286 -0.3135 -0.5382 -0.3174 -0.6582 -0.3217 -0.7892 -0.3266 -0.9324 -0.3321 -1.0888 -0.3383 -1.2597 -0.3454 -1.4467 -0.3534 -1.6515 -0.3627 -1.8766 -0.3735 -2.1249 -0.3864 -2.4002 -0.4025 -2.7076 -0.4238 -3.0542 -0.4624 -3.4494 -0.4754 -3.9069 -0.4774 -4.4464 -0.4798 -5.0967 -0.4825 -5.9022 -0.4858 -6.9333 -0.4897 -8.3061 -0.4944 -10.2236 -0.4999 -13.0617 -0.5066 -17.5742 -0.5151 -25.3165 -0.5285 -39.5658 -0.5642 -58.8907 -0.6853 -46.2382 -0.6678 -20.0858 0.2830 -8.4410 0.8010 -3.5291 0.9690 -1.2744 0.9995 -0.1610 0.9713 0.4162 0.9226 0.7218 0.8650 0.8819 0.8082 0.9610 0.7530 0.9937 0.7018 0.9997 0.6544 0.9902 0.6110 0.9722 0.5710 0.9496 0.5342 0.9250 0.5001 0.8999 0.4681 0.8750 0.4380 0.8510 0.4092 0.8279 0.3813 0.8061 0.3540 0.7853 0.3269 0.7657 0.2999 0.7470 0.2726 0.7293 0.2448 0.7124 0.2163 0.6964 0.1871 0.6811 0.1570 0.6665 0.1259 0.6527 0.0939 0.6396 0.0610 0.6273 0.0274 0.6159 -0.0068 0.6054 -0.0413 0.5959 -0.0756 0.5876 -0.1092 0.5807 -0.1414 0.5752 -0.1716 0.5714 -0.1989 0.5695 -0.2226 0.5699 -0.2423 0.5729 -0.2578 0.5789 -0.2693 0.5892 -0.2773 0.6050 -0.2826 0.6250 -0.2860 0.7117 -0.2880 -0.2190 -0.2891 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 32.000 0.347 0.734 -0.118 0.292 1.000 0.0000 -0.6812 Cpi Cpv ----------------- -0.2039 -0.2862 -0.0956 -0.2862 0.6091 -0.2862 0.5907 -0.2862 0.5688 -0.2862 0.5487 -0.2862 0.5276 -0.2863 0.5058 -0.2864 0.4829 -0.2865 0.4584 -0.2867 0.4323 -0.2869 0.4041 -0.2873 0.3734 -0.2877 0.3401 -0.2882 0.3037 -0.2889 0.2638 -0.2897 0.2201 -0.2907 0.1722 -0.2918 0.1196 -0.2932 0.0618 -0.2947 -0.0017 -0.2965 -0.0714 -0.2986 -0.1479 -0.3009 -0.2318 -0.3035 -0.3238 -0.3065 -0.4245 -0.3098 -0.5349 -0.3136 -0.6556 -0.3178 -0.7876 -0.3225 -0.9320 -0.3277 -1.0898 -0.3337 -1.2624 -0.3404 -1.4513 -0.3481 -1.6586 -0.3568 -1.8865 -0.3669 -2.1381 -0.3789 -2.4174 -0.3936 -2.7296 -0.4127 -3.0818 -0.4421 -3.4840 -0.4690 -3.9500 -0.4710 -4.5000 -0.4733 -5.1636 -0.4760 -5.9863 -0.4792 -7.0404 -0.4830 -8.4448 -0.4875 -10.4081 -0.4929 -13.3168 -0.4994 -17.9461 -0.5075 -25.8989 -0.5198 -40.5610 -0.5522 -60.5355 -0.6663 -47.7010 -0.6812 -20.8260 0.2542 -8.8175 0.7844 -3.7366 0.9625 -1.3960 1.0000 -0.2350 0.9762 0.3705 0.9299 0.6938 0.8744 0.8655 0.8183 0.9523 0.7638 0.9904 0.7129 1.0000 0.6656 0.9931 0.6221 0.9769 0.5819 0.9556 0.5449 0.9319 0.5105 0.9073 0.4782 0.8828 0.4477 0.8590 0.4186 0.8362 0.3903 0.8143 0.3627 0.7936 0.3354 0.7739 0.3080 0.7551 0.2804 0.7373 0.2523 0.7204 0.2236 0.7042 0.1941 0.6888 0.1637 0.6741 0.1324 0.6601 0.1001 0.6469 0.0670 0.6345 0.0331 0.6229 -0.0013 0.6123 -0.0360 0.6027 -0.0706 0.5943 -0.1044 0.5872 -0.1369 0.5816 -0.1673 0.5776 -0.1949 0.5756 -0.2189 0.5758 -0.2388 0.5787 -0.2544 0.5844 -0.2660 0.5945 -0.2741 0.6101 -0.2795 0.6297 -0.2830 0.7153 -0.2850 -0.2039 -0.2862 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 32.500 0.356 0.741 -0.120 0.279 1.000 0.0000 -0.7242 Cpi Cpv ----------------- -0.1887 -0.2857 -0.0818 -0.2857 0.6140 -0.2857 0.5958 -0.2858 0.5741 -0.2858 0.5541 -0.2858 0.5333 -0.2859 0.5115 -0.2859 0.4887 -0.2861 0.4644 -0.2862 0.4384 -0.2865 0.4102 -0.2868 0.3797 -0.2872 0.3464 -0.2878 0.3100 -0.2884 0.2701 -0.2892 0.2264 -0.2902 0.1785 -0.2913 0.1258 -0.2926 0.0679 -0.2941 0.0043 -0.2959 -0.0656 -0.2979 -0.1424 -0.3003 -0.2266 -0.3029 -0.3190 -0.3058 -0.4203 -0.3091 -0.5313 -0.3128 -0.6528 -0.3170 -0.7858 -0.3217 -0.9313 -0.3270 -1.0904 -0.3329 -1.2647 -0.3396 -1.4556 -0.3473 -1.6652 -0.3561 -1.8959 -0.3663 -2.1509 -0.3783 -2.4341 -0.3929 -2.7510 -0.4115 -3.1090 -0.4375 -3.5181 -0.4862 -3.9925 -0.4881 -4.5530 -0.4904 -5.2299 -0.4931 -6.0698 -0.4963 -7.1468 -0.5001 -8.5830 -0.5046 -10.5925 -0.5100 -13.5720 -0.5163 -18.3187 -0.5241 -26.4835 -0.5357 -41.5618 -0.5654 -62.1931 -0.6742 -49.1785 -0.7242 -21.5755 0.2122 -9.1999 0.7576 -3.9481 0.9555 -1.5204 0.9998 -0.3110 0.9823 0.3232 0.9374 0.6646 0.8854 0.8481 0.8293 0.9428 0.7762 0.9863 0.7253 0.9997 0.6781 0.9955 0.6344 0.9812 0.5940 0.9612 0.5566 0.9384 0.5218 0.9145 0.4892 0.8904 0.4582 0.8669 0.4287 0.8442 0.4000 0.8224 0.3720 0.8017 0.3442 0.7820 0.3164 0.7632 0.2884 0.7453 0.2599 0.7282 0.2308 0.7119 0.2009 0.6964 0.1702 0.6816 0.1385 0.6675 0.1058 0.6542 0.0723 0.6416 0.0381 0.6299 0.0032 0.6192 -0.0319 0.6095 -0.0669 0.6009 -0.1011 0.5937 -0.1341 0.5879 -0.1649 0.5838 -0.1929 0.5817 -0.2172 0.5818 -0.2375 0.5844 -0.2534 0.5900 -0.2652 0.5999 -0.2735 0.6151 -0.2790 0.6344 -0.2825 0.7190 -0.2846 -0.1887 -0.2857 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 33.000 0.365 0.746 -0.122 0.273 1.000 0.0000 -0.7498 Cpi Cpv ----------------- -0.1734 -0.2861 -0.0679 -0.2861 0.6189 -0.2861 0.6009 -0.2861 0.5795 -0.2861 0.5596 -0.2861 0.5389 -0.2862 0.5173 -0.2863 0.4947 -0.2864 0.4704 -0.2866 0.4445 -0.2868 0.4164 -0.2872 0.3859 -0.2876 0.3527 -0.2881 0.3164 -0.2888 0.2765 -0.2895 0.2328 -0.2905 0.1848 -0.2916 0.1321 -0.2929 0.0741 -0.2944 0.0103 -0.2962 -0.0597 -0.2982 -0.1367 -0.3004 -0.2213 -0.3030 -0.3141 -0.3060 -0.4159 -0.3093 -0.5275 -0.3130 -0.6497 -0.3172 -0.7836 -0.3219 -0.9302 -0.3272 -1.0908 -0.3331 -1.2667 -0.3399 -1.4595 -0.3476 -1.6714 -0.3565 -1.9049 -0.3668 -2.1631 -0.3790 -2.4503 -0.3937 -2.7719 -0.4122 -3.1356 -0.4372 -3.5516 -0.4904 -4.0344 -0.4951 -4.6054 -0.4974 -5.2956 -0.5001 -6.1528 -0.5032 -7.2528 -0.5070 -8.7208 -0.5114 -10.7765 -0.5167 -13.8272 -0.5228 -18.6921 -0.5303 -27.0701 -0.5410 -42.5679 -0.5682 -63.8629 -0.6713 -50.6704 -0.7498 -22.3343 0.1748 -9.5880 0.7358 -4.1634 0.9468 -1.6475 0.9990 -0.3892 0.9864 0.2743 0.9448 0.6340 0.8947 0.8296 0.8398 0.9324 0.7874 0.9815 0.7367 0.9988 0.6896 0.9974 0.6458 0.9850 0.6052 0.9664 0.5675 0.9446 0.5324 0.9214 0.4994 0.8978 0.4681 0.8746 0.4381 0.8520 0.4090 0.8304 0.3806 0.8097 0.3524 0.7899 0.3243 0.7711 0.2959 0.7532 0.2670 0.7360 0.2375 0.7196 0.2072 0.7040 0.1761 0.6891 0.1440 0.6749 0.1110 0.6614 0.0771 0.6488 0.0424 0.6370 0.0071 0.6261 -0.0284 0.6163 -0.0638 0.6076 -0.0985 0.6002 -0.1319 0.5943 -0.1632 0.5901 -0.1915 0.5878 -0.2163 0.5877 -0.2369 0.5902 -0.2531 0.5956 -0.2652 0.6052 -0.2736 0.6202 -0.2792 0.6392 -0.2828 0.7226 -0.2849 -0.1734 -0.2861 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 33.500 0.356 0.735 -0.123 0.268 1.000 0.0000 -0.7329 Cpi Cpv ----------------- -0.1580 -0.2810 -0.0539 -0.2810 0.6239 -0.2810 0.6060 -0.2810 0.5848 -0.2810 0.5652 -0.2810 0.5446 -0.2811 0.5232 -0.2812 0.5006 -0.2813 0.4765 -0.2815 0.4507 -0.2817 0.4227 -0.2820 0.3923 -0.2824 0.3591 -0.2829 0.3228 -0.2835 0.2830 -0.2843 0.2393 -0.2852 0.1913 -0.2863 0.1385 -0.2876 0.0804 -0.2891 0.0166 -0.2908 -0.0537 -0.2927 -0.1309 -0.2949 -0.2157 -0.2973 -0.3089 -0.3001 -0.4112 -0.3032 -0.5234 -0.3067 -0.6464 -0.3106 -0.7812 -0.3150 -0.9289 -0.3199 -1.0908 -0.3254 -1.2683 -0.3316 -1.4631 -0.3387 -1.6773 -0.3467 -1.9135 -0.3559 -2.1750 -0.3667 -2.4661 -0.3796 -2.7924 -0.3957 -3.1616 -0.4172 -3.5845 -0.4576 -4.0757 -0.4692 -4.6572 -0.4714 -5.3607 -0.4740 -6.2351 -0.4770 -7.3582 -0.4807 -8.8581 -0.4850 -10.9601 -0.4900 -14.0824 -0.4959 -19.0659 -0.5028 -27.6586 -0.5127 -43.5791 -0.5370 -65.5446 -0.6332 -52.1762 -0.7329 -23.1019 0.1591 -9.9817 0.7230 -4.3825 0.9407 -1.7774 0.9980 -0.4693 0.9891 0.2238 0.9501 0.6023 0.9017 0.8100 0.8480 0.9212 0.7963 0.9760 0.7460 0.9974 0.6992 0.9988 0.6554 0.9884 0.6148 0.9713 0.5771 0.9505 0.5418 0.9280 0.5086 0.9049 0.4770 0.8820 0.4468 0.8597 0.4176 0.8382 0.3889 0.8175 0.3605 0.7978 0.3321 0.7790 0.3035 0.7609 0.2745 0.7437 0.2448 0.7273 0.2143 0.7115 0.1830 0.6965 0.1508 0.6822 0.1177 0.6687 0.0836 0.6559 0.0488 0.6440 0.0135 0.6330 -0.0222 0.6231 -0.0577 0.6142 -0.0925 0.6068 -0.1260 0.6008 -0.1574 0.5964 -0.1859 0.5939 -0.2107 0.5937 -0.2314 0.5960 -0.2477 0.6012 -0.2599 0.6106 -0.2683 0.6253 -0.2740 0.6440 -0.2776 0.7262 -0.2798 -0.1580 -0.2810 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 34.000 0.356 0.732 -0.124 0.259 1.000 0.0000 -0.7336 Cpi Cpv ----------------- -0.1426 -0.2788 -0.0399 -0.2788 0.6289 -0.2788 0.6112 -0.2788 0.5902 -0.2789 0.5707 -0.2789 0.5503 -0.2789 0.5290 -0.2790 0.5066 -0.2791 0.4826 -0.2793 0.4569 -0.2795 0.4290 -0.2799 0.3987 -0.2803 0.3655 -0.2808 0.3293 -0.2814 0.2895 -0.2821 0.2459 -0.2830 0.1978 -0.2841 0.1450 -0.2853 0.0869 -0.2868 0.0229 -0.2884 -0.0475 -0.2903 -0.1249 -0.2924 -0.2100 -0.2948 -0.3036 -0.2975 -0.4064 -0.3006 -0.5191 -0.3040 -0.6429 -0.3078 -0.7786 -0.3120 -0.9274 -0.3167 -1.0905 -0.3220 -1.2696 -0.3280 -1.4663 -0.3347 -1.6827 -0.3423 -1.9216 -0.3510 -2.1863 -0.3612 -2.4813 -0.3732 -2.8123 -0.3881 -3.1871 -0.4076 -3.6168 -0.4394 -4.1165 -0.4606 -4.7084 -0.4628 -5.4252 -0.4653 -6.3168 -0.4682 -7.4629 -0.4718 -8.9949 -0.4760 -11.1434 -0.4809 -14.3374 -0.4865 -19.4402 -0.4932 -28.2489 -0.5023 -44.5951 -0.5243 -67.2375 -0.6146 -53.6954 -0.7336 -23.8783 0.1325 -10.3809 0.7052 -4.6054 0.9324 -1.9100 0.9963 -0.5515 0.9919 0.1717 0.9559 0.5692 0.9093 0.7895 0.8569 0.9091 0.8060 0.9698 0.7561 0.9953 0.7095 0.9996 0.6658 0.9914 0.6251 0.9758 0.5872 0.9561 0.5516 0.9343 0.5182 0.9118 0.4864 0.8893 0.4559 0.8672 0.4263 0.8458 0.3973 0.8253 0.3686 0.8056 0.3399 0.7867 0.3110 0.7686 0.2817 0.7514 0.2517 0.7348 0.2210 0.7190 0.1894 0.7039 0.1569 0.6895 0.1235 0.6759 0.0892 0.6630 0.0541 0.6510 0.0185 0.6399 -0.0174 0.6298 -0.0532 0.6209 -0.0883 0.6133 -0.1221 0.6072 -0.1538 0.6027 -0.1825 0.6001 -0.2077 0.5997 -0.2286 0.6018 -0.2451 0.6068 -0.2574 0.6160 -0.2660 0.6304 -0.2717 0.6488 -0.2754 0.7299 -0.2776 -0.1426 -0.2788 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 34.500 0.359 0.732 -0.126 0.250 1.000 0.0000 -0.7422 Cpi Cpv ----------------- -0.1271 -0.2773 -0.0258 -0.2773 0.6339 -0.2773 0.6164 -0.2773 0.5956 -0.2773 0.5763 -0.2774 0.5561 -0.2774 0.5349 -0.2775 0.5127 -0.2776 0.4888 -0.2778 0.4632 -0.2780 0.4354 -0.2783 0.4051 -0.2787 0.3721 -0.2792 0.3359 -0.2798 0.2962 -0.2805 0.2525 -0.2814 0.2045 -0.2825 0.1516 -0.2837 0.0934 -0.2851 0.0294 -0.2867 -0.0412 -0.2886 -0.1188 -0.2906 -0.2042 -0.2930 -0.2981 -0.2957 -0.4013 -0.2986 -0.5146 -0.3019 -0.6391 -0.3057 -0.7756 -0.3098 -0.9255 -0.3144 -1.0899 -0.3196 -1.2705 -0.3254 -1.4691 -0.3319 -1.6878 -0.3393 -1.9293 -0.3478 -2.1973 -0.3576 -2.4960 -0.3692 -2.8316 -0.3834 -3.2121 -0.4016 -3.6485 -0.4289 -4.1566 -0.4613 -4.7589 -0.4634 -5.4890 -0.4659 -6.3979 -0.4688 -7.5670 -0.4723 -9.1310 -0.4764 -11.3262 -0.4812 -14.5922 -0.4868 -19.8149 -0.4931 -28.8406 -0.5016 -45.6154 -0.5216 -68.9411 -0.6068 -55.2275 -0.7422 -24.6631 0.1000 -10.7855 0.6842 -4.8318 0.9226 -2.0451 0.9939 -0.6357 0.9944 0.1181 0.9618 0.5349 0.9172 0.7679 0.8661 0.8962 0.8160 0.9628 0.7666 0.9926 0.7202 1.0000 0.6765 0.9939 0.6357 0.9799 0.5976 0.9613 0.5618 0.9404 0.5281 0.9184 0.4960 0.8963 0.4652 0.8745 0.4353 0.8533 0.4060 0.8328 0.3769 0.8132 0.3480 0.7943 0.3187 0.7762 0.2891 0.7589 0.2588 0.7423 0.2278 0.7265 0.1959 0.7113 0.1631 0.6968 0.1294 0.6831 0.0947 0.6701 0.0594 0.6580 0.0234 0.6468 -0.0128 0.6366 -0.0490 0.6276 -0.0844 0.6199 -0.1185 0.6136 -0.1505 0.6090 -0.1797 0.6062 -0.2051 0.6057 -0.2263 0.6076 -0.2430 0.6125 -0.2555 0.6214 -0.2642 0.6356 -0.2701 0.6537 -0.2738 0.7336 -0.2761 -0.1271 -0.2773 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 35.000 0.367 0.738 -0.127 0.241 1.000 0.0000 -0.7631 Cpi Cpv ----------------- -0.1115 -0.2768 -0.0117 -0.2768 0.6389 -0.2768 0.6216 -0.2768 0.6011 -0.2768 0.5819 -0.2768 0.5619 -0.2769 0.5409 -0.2769 0.5187 -0.2771 0.4950 -0.2772 0.4695 -0.2774 0.4418 -0.2777 0.4116 -0.2781 0.3786 -0.2786 0.3425 -0.2792 0.3029 -0.2799 0.2592 -0.2808 0.2112 -0.2818 0.1584 -0.2830 0.1001 -0.2844 0.0360 -0.2860 -0.0347 -0.2878 -0.1125 -0.2899 -0.1982 -0.2922 -0.2924 -0.2948 -0.3960 -0.2978 -0.5099 -0.3011 -0.6350 -0.3048 -0.7724 -0.3089 -0.9233 -0.3135 -1.0890 -0.3187 -1.2711 -0.3245 -1.4715 -0.3310 -1.6924 -0.3385 -1.9366 -0.3471 -2.2077 -0.3570 -2.5103 -0.3687 -2.8504 -0.3829 -3.2365 -0.4010 -3.6797 -0.4264 -4.1960 -0.4752 -4.8088 -0.4773 -5.5521 -0.4797 -6.4782 -0.4827 -7.6704 -0.4861 -9.2665 -0.4902 -11.5084 -0.4950 -14.8467 -0.5005 -20.1897 -0.5067 -29.4336 -0.5147 -46.6399 -0.5329 -70.6549 -0.6138 -56.7721 -0.7631 -25.4562 0.0587 -11.1953 0.6588 -5.0619 0.9106 -2.1829 0.9906 -0.7219 0.9967 0.0629 0.9677 0.4994 0.9254 0.7453 0.8758 0.8824 0.8265 0.9552 0.7776 0.9893 0.7314 0.9998 0.6877 0.9960 0.6469 0.9836 0.6085 0.9662 0.5725 0.9462 0.5385 0.9248 0.5061 0.9031 0.4749 0.8816 0.4446 0.8606 0.4150 0.8403 0.3856 0.8207 0.3562 0.8018 0.3267 0.7838 0.2966 0.7664 0.2660 0.7498 0.2346 0.7338 0.2024 0.7186 0.1692 0.7040 0.1352 0.6902 0.1002 0.6772 0.0644 0.6649 0.0281 0.6536 -0.0086 0.6434 -0.0451 0.6342 -0.0810 0.6264 -0.1155 0.6200 -0.1480 0.6153 -0.1775 0.6124 -0.2033 0.6117 -0.2248 0.6135 -0.2418 0.6181 -0.2545 0.6269 -0.2634 0.6407 -0.2694 0.6585 -0.2732 0.7373 -0.2755 -0.1115 -0.2768 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 35.500 0.381 0.745 -0.129 0.236 1.000 0.0000 -0.7830 Cpi Cpv ----------------- -0.0959 -0.2785 0.0025 -0.2785 0.6439 -0.2785 0.6269 -0.2785 0.6065 -0.2785 0.5876 -0.2785 0.5677 -0.2786 0.5468 -0.2787 0.5248 -0.2788 0.5012 -0.2790 0.4758 -0.2792 0.4482 -0.2795 0.4182 -0.2799 0.3853 -0.2804 0.3493 -0.2810 0.3096 -0.2817 0.2660 -0.2826 0.2181 -0.2836 0.1652 -0.2848 0.1069 -0.2862 0.0427 -0.2878 -0.0281 -0.2896 -0.1061 -0.2916 -0.1920 -0.2940 -0.2865 -0.2966 -0.3906 -0.2996 -0.5050 -0.3030 -0.6307 -0.3067 -0.7689 -0.3110 -0.9208 -0.3157 -1.0878 -0.3210 -1.2714 -0.3270 -1.4735 -0.3338 -1.6966 -0.3416 -1.9434 -0.3506 -2.2177 -0.3610 -2.5240 -0.3734 -2.8687 -0.3884 -3.2602 -0.4073 -3.7102 -0.4331 -4.2349 -0.4896 -4.8580 -0.4931 -5.6145 -0.4956 -6.5578 -0.4985 -7.7732 -0.5020 -9.4014 -0.5061 -11.6901 -0.5109 -15.1008 -0.5163 -20.5646 -0.5223 -30.0279 -0.5298 -47.6681 -0.5466 -72.3785 -0.6231 -58.3287 -0.7830 -26.2572 0.0160 -11.6102 0.6319 -5.2954 0.8975 -2.3233 0.9864 -0.8100 0.9984 0.0062 0.9732 0.4626 0.9331 0.7217 0.8852 0.8678 0.8367 0.9468 0.7884 0.9854 0.7424 0.9991 0.6988 0.9977 0.6578 0.9870 0.6193 0.9708 0.5830 0.9517 0.5486 0.9310 0.5158 0.9097 0.4843 0.8885 0.4536 0.8678 0.4236 0.8476 0.3938 0.8280 0.3641 0.8092 0.3341 0.7912 0.3037 0.7738 0.2726 0.7571 0.2408 0.7411 0.2082 0.7258 0.1746 0.7112 0.1401 0.6973 0.1046 0.6842 0.0684 0.6719 0.0316 0.6605 -0.0056 0.6501 -0.0426 0.6409 -0.0790 0.6330 -0.1141 0.6265 -0.1471 0.6216 -0.1772 0.6186 -0.2035 0.6177 -0.2254 0.6193 -0.2428 0.6238 -0.2558 0.6323 -0.2649 0.6459 -0.2710 0.6634 -0.2749 0.7410 -0.2772 -0.0959 -0.2785 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 36.000 0.371 0.734 -0.130 0.234 1.000 0.0000 -0.7495 Cpi Cpv ----------------- -0.0802 -0.2741 0.0168 -0.2741 0.6490 -0.2741 0.6321 -0.2741 0.6120 -0.2741 0.5932 -0.2742 0.5735 -0.2742 0.5528 -0.2743 0.5310 -0.2744 0.5075 -0.2746 0.4822 -0.2748 0.4547 -0.2751 0.4248 -0.2754 0.3920 -0.2759 0.3560 -0.2765 0.3165 -0.2772 0.2729 -0.2780 0.2250 -0.2790 0.1721 -0.2801 0.1138 -0.2814 0.0495 -0.2830 -0.0214 -0.2848 -0.0995 -0.2868 -0.1856 -0.2890 -0.2805 -0.2915 -0.3849 -0.2944 -0.4998 -0.2975 -0.6262 -0.3011 -0.7652 -0.3050 -0.9181 -0.3094 -1.0862 -0.3143 -1.2713 -0.3199 -1.4752 -0.3261 -1.7004 -0.3331 -1.9498 -0.3412 -2.2271 -0.3506 -2.5372 -0.3615 -2.8865 -0.3746 -3.2835 -0.3911 -3.7401 -0.4133 -4.2730 -0.4590 -4.9066 -0.4669 -5.6762 -0.4692 -6.6368 -0.4721 -7.8751 -0.4754 -9.5355 -0.4794 -11.8712 -0.4840 -15.3545 -0.4892 -20.9395 -0.4949 -30.6231 -0.5019 -48.6999 -0.5169 -74.1112 -0.5872 -59.8969 -0.7495 -27.0660 0.0041 -12.0301 0.6186 -5.5324 0.8895 -2.4661 0.9834 -0.9000 0.9992 -0.0520 0.9768 0.4246 0.9386 0.6971 0.8921 0.8523 0.8445 0.9378 0.7967 0.9809 0.7511 0.9980 0.7077 0.9989 0.6668 0.9899 0.6282 0.9751 0.5919 0.9569 0.5574 0.9369 0.5244 0.9161 0.4927 0.8953 0.4619 0.8747 0.4316 0.8547 0.4017 0.8353 0.3717 0.8165 0.3415 0.7985 0.3109 0.7811 0.2797 0.7644 0.2477 0.7484 0.2149 0.7330 0.1812 0.7184 0.1465 0.7044 0.1109 0.6912 0.0745 0.6788 0.0376 0.6673 0.0003 0.6569 -0.0369 0.6475 -0.0735 0.6395 -0.1087 0.6329 -0.1419 0.6279 -0.1720 0.6248 -0.1985 0.6238 -0.2206 0.6252 -0.2381 0.6295 -0.2512 0.6378 -0.2603 0.6511 -0.2665 0.6683 -0.2704 0.7448 -0.2728 -0.0802 -0.2741 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 36.500 0.369 0.729 -0.132 0.228 1.000 0.0000 -0.7281 Cpi Cpv ----------------- -0.0645 -0.2722 0.0311 -0.2722 0.6541 -0.2722 0.6374 -0.2722 0.6175 -0.2722 0.5989 -0.2723 0.5794 -0.2723 0.5589 -0.2724 0.5371 -0.2725 0.5138 -0.2727 0.4887 -0.2729 0.4613 -0.2732 0.4314 -0.2735 0.3987 -0.2740 0.3629 -0.2746 0.3234 -0.2752 0.2799 -0.2761 0.2320 -0.2770 0.1791 -0.2782 0.1208 -0.2795 0.0565 -0.2810 -0.0145 -0.2827 -0.0928 -0.2847 -0.1791 -0.2869 -0.2742 -0.2893 -0.3790 -0.2921 -0.4944 -0.2952 -0.6214 -0.2986 -0.7612 -0.3024 -0.9150 -0.3066 -1.0844 -0.3113 -1.2708 -0.3166 -1.4765 -0.3225 -1.7038 -0.3292 -1.9558 -0.3368 -2.2362 -0.3454 -2.5499 -0.3555 -2.9036 -0.3676 -3.3061 -0.3826 -3.7694 -0.4025 -4.3105 -0.4384 -4.9544 -0.4533 -5.7372 -0.4557 -6.7149 -0.4584 -7.9764 -0.4617 -9.6689 -0.4655 -12.0515 -0.4701 -15.6076 -0.4751 -21.3142 -0.4807 -31.2190 -0.4872 -49.7348 -0.5007 -75.8526 -0.5654 -61.4761 -0.7281 -27.8822 -0.0157 -12.4549 0.6011 -5.7728 0.8796 -2.6114 0.9795 -0.9919 0.9998 -0.1117 0.9806 0.3854 0.9443 0.6715 0.8993 0.8360 0.8526 0.9280 0.8055 0.9758 0.7602 0.9963 0.7170 0.9997 0.6761 0.9925 0.6375 0.9790 0.6010 0.9618 0.5664 0.9425 0.5332 0.9223 0.5013 0.9018 0.4702 0.8815 0.4397 0.8617 0.4094 0.8424 0.3792 0.8237 0.3488 0.8057 0.3179 0.7883 0.2864 0.7716 0.2542 0.7556 0.2211 0.7402 0.1871 0.7254 0.1522 0.7114 0.1163 0.6981 0.0797 0.6857 0.0424 0.6742 0.0049 0.6636 -0.0326 0.6542 -0.0695 0.6461 -0.1050 0.6393 -0.1384 0.6342 -0.1689 0.6310 -0.1956 0.6298 -0.2180 0.6311 -0.2357 0.6352 -0.2489 0.6433 -0.2582 0.6563 -0.2645 0.6732 -0.2685 0.7485 -0.2709 -0.0645 -0.2722 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 37.000 0.370 0.727 -0.134 0.220 1.000 0.0000 -0.7153 Cpi Cpv ----------------- -0.0487 -0.2710 0.0454 -0.2710 0.6591 -0.2710 0.6427 -0.2710 0.6231 -0.2710 0.6046 -0.2711 0.5853 -0.2711 0.5649 -0.2712 0.5433 -0.2713 0.5202 -0.2715 0.4951 -0.2717 0.4679 -0.2720 0.4381 -0.2723 0.4055 -0.2728 0.3698 -0.2733 0.3304 -0.2740 0.2869 -0.2748 0.2391 -0.2758 0.1862 -0.2769 0.1279 -0.2782 0.0636 -0.2797 -0.0075 -0.2814 -0.0859 -0.2833 -0.1724 -0.2855 -0.2678 -0.2879 -0.3729 -0.2906 -0.4888 -0.2936 -0.6164 -0.2969 -0.7569 -0.3006 -0.9117 -0.3047 -1.0822 -0.3093 -1.2700 -0.3145 -1.4774 -0.3202 -1.7068 -0.3267 -1.9613 -0.3340 -2.2447 -0.3423 -2.5621 -0.3520 -2.9203 -0.3634 -3.3281 -0.3775 -3.7980 -0.3960 -4.3474 -0.4256 -5.0015 -0.4493 -5.7974 -0.4515 -6.7923 -0.4542 -8.0768 -0.4575 -9.8014 -0.4613 -12.2311 -0.4657 -15.8601 -0.4707 -21.6887 -0.4762 -31.8156 -0.4823 -50.7726 -0.4946 -77.6021 -0.5541 -63.0659 -0.7153 -28.7057 -0.0416 -12.8844 0.5803 -6.0164 0.8679 -2.7592 0.9748 -1.0857 1.0000 -0.1729 0.9843 0.3450 0.9500 0.6449 0.9069 0.8189 0.8608 0.9176 0.8146 0.9702 0.7696 0.9940 0.7266 1.0000 0.6858 0.9947 0.6471 0.9826 0.6105 0.9664 0.5756 0.9479 0.5423 0.9282 0.5101 0.9082 0.4787 0.8882 0.4479 0.8685 0.4174 0.8494 0.3869 0.8308 0.3562 0.8128 0.3250 0.7955 0.2933 0.7788 0.2608 0.7627 0.2274 0.7473 0.1931 0.7325 0.1578 0.7184 0.1217 0.7051 0.0847 0.6926 0.0472 0.6809 0.0093 0.6703 -0.0285 0.6608 -0.0657 0.6526 -0.1016 0.6458 -0.1354 0.6405 -0.1663 0.6372 -0.1933 0.6359 -0.2160 0.6370 -0.2339 0.6409 -0.2474 0.6488 -0.2568 0.6615 -0.2631 0.6781 -0.2672 0.7523 -0.2697 -0.0487 -0.2710 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 37.500 0.373 0.727 -0.135 0.212 1.000 0.0000 -0.7076 Cpi Cpv ----------------- -0.0328 -0.2699 0.0598 -0.2699 0.6642 -0.2699 0.6480 -0.2699 0.6286 -0.2699 0.6104 -0.2699 0.5912 -0.2700 0.5710 -0.2700 0.5496 -0.2701 0.5265 -0.2703 0.5016 -0.2705 0.4745 -0.2708 0.4449 -0.2711 0.4124 -0.2716 0.3767 -0.2721 0.3374 -0.2728 0.2941 -0.2736 0.2463 -0.2745 0.1935 -0.2757 0.1352 -0.2769 0.0708 -0.2784 -0.0004 -0.2801 -0.0789 -0.2819 -0.1656 -0.2840 -0.2612 -0.2864 -0.3667 -0.2891 -0.4830 -0.2920 -0.6112 -0.2953 -0.7524 -0.2989 -0.9081 -0.3030 -1.0797 -0.3075 -1.2689 -0.3125 -1.4780 -0.3181 -1.7094 -0.3245 -1.9663 -0.3316 -2.2527 -0.3397 -2.5738 -0.3491 -2.9363 -0.3603 -3.3495 -0.3738 -3.8260 -0.3913 -4.3835 -0.4173 -5.0478 -0.4517 -5.8569 -0.4539 -6.8688 -0.4566 -8.1763 -0.4598 -9.9332 -0.4636 -12.4099 -0.4680 -16.1120 -0.4729 -22.0628 -0.4782 -32.4127 -0.4842 -51.8129 -0.4953 -79.3591 -0.5500 -64.6658 -0.7076 -29.5361 -0.0736 -13.3185 0.5581 -6.2633 0.8531 -2.9093 0.9704 -1.1812 0.9998 -0.2355 0.9881 0.3034 0.9553 0.6173 0.9146 0.8010 0.8691 0.9065 0.8239 0.9639 0.7792 0.9913 0.7364 0.9999 0.6956 0.9966 0.6569 0.9859 0.6202 0.9707 0.5852 0.9530 0.5516 0.9339 0.5191 0.9143 0.4875 0.8946 0.4564 0.8752 0.4257 0.8562 0.3949 0.8377 0.3638 0.8198 0.3324 0.8025 0.3003 0.7858 0.2675 0.7697 0.2338 0.7543 0.1992 0.7395 0.1637 0.7254 0.1272 0.7120 0.0900 0.6994 0.0520 0.6877 0.0138 0.6770 -0.0244 0.6674 -0.0619 0.6591 -0.0982 0.6522 -0.1324 0.6468 -0.1636 0.6434 -0.1910 0.6419 -0.2139 0.6429 -0.2322 0.6466 -0.2458 0.6543 -0.2554 0.6668 -0.2618 0.6830 -0.2660 0.7560 -0.2685 -0.0328 -0.2699 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 38.000 0.381 0.731 -0.137 0.205 1.000 0.0000 -0.7130 Cpi Cpv ----------------- -0.0170 -0.2693 0.0742 -0.2693 0.6694 -0.2693 0.6533 -0.2693 0.6342 -0.2693 0.6161 -0.2693 0.5971 -0.2694 0.5771 -0.2694 0.5558 -0.2695 0.5329 -0.2697 0.5082 -0.2699 0.4812 -0.2702 0.4517 -0.2705 0.4193 -0.2709 0.3837 -0.2715 0.3445 -0.2721 0.3013 -0.2729 0.2535 -0.2738 0.2008 -0.2749 0.1425 -0.2761 0.0781 -0.2776 0.0069 -0.2792 -0.0717 -0.2811 -0.1586 -0.2832 -0.2544 -0.2855 -0.3602 -0.2882 -0.4770 -0.2911 -0.6057 -0.2943 -0.7476 -0.2980 -0.9042 -0.3020 -1.0768 -0.3065 -1.2674 -0.3116 -1.4781 -0.3172 -1.7116 -0.3236 -1.9709 -0.3308 -2.2603 -0.3391 -2.5849 -0.3487 -2.9518 -0.3600 -3.3703 -0.3738 -3.8533 -0.3914 -4.4189 -0.4161 -5.0935 -0.4660 -5.9155 -0.4682 -6.9445 -0.4709 -8.2751 -0.4741 -10.0640 -0.4778 -12.5878 -0.4823 -16.3631 -0.4872 -22.4365 -0.4925 -33.0099 -0.4982 -52.8555 -0.5085 -81.1232 -0.5590 -66.2753 -0.7130 -30.3733 -0.1124 -13.7571 0.5304 -6.5133 0.8374 -3.0617 0.9637 -1.2786 0.9990 -0.2995 0.9912 0.2607 0.9612 0.5888 0.9222 0.7822 0.8779 0.8946 0.8335 0.9570 0.7892 0.9881 0.7466 0.9993 0.7059 0.9980 0.6672 0.9888 0.6303 0.9747 0.5951 0.9578 0.5612 0.9394 0.5285 0.9202 0.4967 0.9009 0.4653 0.8817 0.4342 0.8629 0.4031 0.8446 0.3718 0.8267 0.3400 0.8095 0.3076 0.7928 0.2745 0.7767 0.2405 0.7612 0.2055 0.7464 0.1696 0.7323 0.1328 0.7188 0.0952 0.7062 0.0569 0.6945 0.0183 0.6837 -0.0203 0.6740 -0.0583 0.6656 -0.0950 0.6586 -0.1296 0.6532 -0.1612 0.6495 -0.1890 0.6480 -0.2124 0.6488 -0.2309 0.6524 -0.2448 0.6598 -0.2545 0.6720 -0.2611 0.6879 -0.2653 0.7598 -0.2679 -0.0170 -0.2693 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 39.000 0.386 0.727 -0.140 0.199 1.000 0.0000 -0.6785 Cpi Cpv ----------------- 0.0148 -0.2674 0.1031 -0.2674 0.6796 -0.2674 0.6640 -0.2674 0.6453 -0.2674 0.6277 -0.2675 0.6090 -0.2675 0.5893 -0.2676 0.5684 -0.2677 0.5458 -0.2678 0.5213 -0.2680 0.4946 -0.2683 0.4654 -0.2686 0.4333 -0.2691 0.3979 -0.2696 0.3589 -0.2702 0.3158 -0.2710 0.2683 -0.2719 0.2156 -0.2729 0.1574 -0.2741 0.0930 -0.2755 0.0218 -0.2771 -0.0570 -0.2789 -0.1441 -0.2809 -0.2404 -0.2832 -0.3468 -0.2857 -0.4643 -0.2886 -0.5940 -0.2917 -0.7373 -0.2952 -0.8955 -0.2991 -1.0702 -0.3034 -1.2634 -0.3083 -1.4774 -0.3137 -1.7147 -0.3198 -1.9788 -0.3266 -2.2739 -0.3345 -2.6056 -0.3436 -2.9811 -0.3543 -3.4101 -0.3672 -3.9060 -0.3833 -4.4877 -0.4054 -5.1824 -0.4523 -6.0304 -0.4592 -7.0934 -0.4618 -8.4698 -0.4648 -10.3230 -0.4685 -12.9409 -0.4728 -16.8627 -0.4776 -23.1818 -0.4827 -34.2045 -0.4879 -54.9460 -0.4963 -84.6705 -0.5378 -69.5211 -0.6785 -32.0669 -0.1608 -14.6471 0.4865 -7.0225 0.8106 -3.3734 0.9511 -1.4787 0.9963 -0.4319 0.9955 0.1717 0.9705 0.5289 0.9349 0.7423 0.8929 0.8689 0.8501 0.9416 0.8067 0.9801 0.7648 0.9969 0.7243 0.9997 0.6856 0.9936 0.6486 0.9819 0.6131 0.9668 0.5789 0.9497 0.5458 0.9315 0.5135 0.9129 0.4816 0.8943 0.4500 0.8759 0.4184 0.8578 0.3865 0.8402 0.3542 0.8231 0.3213 0.8065 0.2876 0.7904 0.2530 0.7750 0.2175 0.7601 0.1810 0.7459 0.1435 0.7324 0.1052 0.7197 0.0663 0.7079 0.0270 0.6970 -0.0123 0.6872 -0.0510 0.6786 -0.0885 0.6714 -0.1239 0.6658 -0.1563 0.6619 -0.1848 0.6601 -0.2087 0.6607 -0.2278 0.6639 -0.2421 0.6708 -0.2522 0.6825 -0.2590 0.6978 -0.2633 0.7673 -0.2660 0.0148 -0.2674 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 39.500 0.383 0.722 -0.142 0.195 1.000 0.0000 -0.6513 Cpi Cpv ----------------- 0.0308 -0.2662 0.1176 -0.2662 0.6848 -0.2662 0.6694 -0.2662 0.6509 -0.2662 0.6335 -0.2663 0.6150 -0.2663 0.5955 -0.2664 0.5747 -0.2665 0.5523 -0.2666 0.5280 -0.2668 0.5014 -0.2671 0.4723 -0.2674 0.4403 -0.2678 0.4051 -0.2683 0.3662 -0.2690 0.3232 -0.2697 0.2757 -0.2706 0.2232 -0.2717 0.1650 -0.2729 0.1007 -0.2742 0.0294 -0.2758 -0.0494 -0.2776 -0.1366 -0.2796 -0.2331 -0.2818 -0.3397 -0.2843 -0.4576 -0.2870 -0.5878 -0.2901 -0.7317 -0.2935 -0.8907 -0.2973 -1.0665 -0.3014 -1.2609 -0.3061 -1.4764 -0.3112 -1.7156 -0.3170 -1.9821 -0.3236 -2.2800 -0.3310 -2.6152 -0.3394 -2.9948 -0.3493 -3.4290 -0.3611 -3.9313 -0.3759 -4.5209 -0.3957 -5.2257 -0.4337 -6.0866 -0.4459 -7.1665 -0.4484 -8.5658 -0.4514 -10.4510 -0.4550 -13.1160 -0.4592 -17.1111 -0.4639 -23.5534 -0.4688 -34.8014 -0.4737 -55.9933 -0.4813 -86.4525 -0.5186 -71.1565 -0.6513 -32.9228 -0.1776 -15.0982 0.4675 -7.2815 0.7981 -3.5326 0.9447 -1.5813 0.9945 -0.5002 0.9971 0.1255 0.9745 0.4975 0.9405 0.7212 0.8997 0.8550 0.8576 0.9329 0.8148 0.9754 0.7732 0.9950 0.7329 1.0000 0.6943 0.9955 0.6572 0.9851 0.6217 0.9709 0.5874 0.9545 0.5541 0.9369 0.5215 0.9187 0.4895 0.9004 0.4576 0.8822 0.4258 0.8643 0.3937 0.8468 0.3611 0.8297 0.3279 0.8132 0.2939 0.7972 0.2591 0.7817 0.2233 0.7669 0.1865 0.7527 0.1488 0.7392 0.1103 0.7264 0.0710 0.7145 0.0314 0.7036 -0.0083 0.6937 -0.0473 0.6851 -0.0851 0.6778 -0.1209 0.6721 -0.1536 0.6681 -0.1824 0.6662 -0.2067 0.6666 -0.2260 0.6696 -0.2405 0.6764 -0.2507 0.6878 -0.2576 0.7028 -0.2621 0.7711 -0.2647 0.0308 -0.2662 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 40.000 0.384 0.719 -0.144 0.189 1.000 0.0000 -0.6333 Cpi Cpv ----------------- 0.0467 -0.2655 0.1321 -0.2655 0.6899 -0.2655 0.6747 -0.2655 0.6565 -0.2655 0.6393 -0.2655 0.6210 -0.2656 0.6017 -0.2656 0.5811 -0.2657 0.5588 -0.2659 0.5346 -0.2661 0.5082 -0.2663 0.4792 -0.2667 0.4474 -0.2671 0.4123 -0.2676 0.3735 -0.2682 0.3307 -0.2690 0.2833 -0.2699 0.2308 -0.2709 0.1727 -0.2721 0.1084 -0.2734 0.0371 -0.2750 -0.0417 -0.2767 -0.1290 -0.2787 -0.2256 -0.2809 -0.3325 -0.2833 -0.4507 -0.2860 -0.5814 -0.2890 -0.7259 -0.2924 -0.8857 -0.2961 -1.0624 -0.3001 -1.2581 -0.3047 -1.4750 -0.3097 -1.7161 -0.3153 -1.9849 -0.3217 -2.2856 -0.3288 -2.6242 -0.3369 -3.0080 -0.3463 -3.4473 -0.3576 -3.9559 -0.3714 -4.5535 -0.3898 -5.2682 -0.4213 -6.1419 -0.4402 -7.2387 -0.4426 -8.6607 -0.4456 -10.5779 -0.4491 -13.2900 -0.4532 -17.3584 -0.4579 -23.9239 -0.4627 -35.3979 -0.4673 -57.0416 -0.4741 -88.2394 -0.5077 -72.7995 -0.6333 -33.7844 -0.1998 -15.5533 0.4453 -7.5433 0.7839 -3.6939 0.9374 -1.6857 0.9921 -0.5698 0.9983 0.0782 0.9784 0.4652 0.9461 0.6992 0.9066 0.8405 0.8654 0.9237 0.8231 0.9701 0.7818 0.9927 0.7417 0.9999 0.7032 0.9971 0.6661 0.9879 0.6304 0.9747 0.5960 0.9590 0.5625 0.9420 0.5298 0.9242 0.4975 0.9062 0.4654 0.8883 0.4333 0.8706 0.4010 0.8532 0.3681 0.8363 0.3347 0.8198 0.3004 0.8039 0.2653 0.7884 0.2292 0.7736 0.1922 0.7594 0.1541 0.7458 0.1152 0.7331 0.0757 0.7211 0.0357 0.7102 -0.0043 0.7002 -0.0438 0.6915 -0.0820 0.6842 -0.1181 0.6784 -0.1512 0.6743 -0.1804 0.6722 -0.2050 0.6725 -0.2246 0.6754 -0.2394 0.6819 -0.2497 0.6930 -0.2567 0.7077 -0.2613 0.7749 -0.2640 0.0467 -0.2655 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 40.500 0.386 0.717 -0.146 0.183 1.000 0.0000 -0.6211 Cpi Cpv ----------------- 0.0627 -0.2647 0.1466 -0.2647 0.6951 -0.2647 0.6801 -0.2647 0.6621 -0.2647 0.6451 -0.2647 0.6270 -0.2648 0.6078 -0.2648 0.5874 -0.2649 0.5653 -0.2651 0.5413 -0.2653 0.5150 -0.2655 0.4862 -0.2658 0.4545 -0.2663 0.4196 -0.2668 0.3809 -0.2674 0.3382 -0.2681 0.2909 -0.2690 0.2385 -0.2700 0.1805 -0.2712 0.1162 -0.2725 0.0450 -0.2741 -0.0339 -0.2758 -0.1213 -0.2777 -0.2180 -0.2799 -0.3251 -0.2823 -0.4437 -0.2850 -0.5748 -0.2879 -0.7198 -0.2912 -0.8803 -0.2948 -1.0580 -0.2988 -1.2549 -0.3033 -1.4733 -0.3082 -1.7162 -0.3137 -1.9872 -0.3199 -2.2907 -0.3268 -2.6326 -0.3347 -3.0206 -0.3439 -3.4650 -0.3547 -3.9799 -0.3680 -4.5852 -0.3853 -5.3099 -0.4126 -6.1964 -0.4390 -7.3099 -0.4414 -8.7547 -0.4443 -10.7038 -0.4478 -13.4628 -0.4519 -17.6045 -0.4565 -24.2935 -0.4611 -35.9937 -0.4655 -58.0905 -0.4716 -90.0307 -0.5019 -74.4496 -0.6211 -34.6514 -0.2254 -16.0122 0.4209 -7.8078 0.7683 -3.8573 0.9292 -1.7916 0.9892 -0.6407 0.9993 0.0298 0.9820 0.4319 0.9516 0.6765 0.9135 0.8252 0.8731 0.9139 0.8315 0.9643 0.7905 0.9899 0.7507 0.9994 0.7122 0.9983 0.6751 0.9905 0.6393 0.9782 0.6048 0.9634 0.5711 0.9469 0.5382 0.9296 0.5057 0.9120 0.4734 0.8943 0.4410 0.8768 0.4084 0.8596 0.3753 0.8427 0.3416 0.8263 0.3071 0.8104 0.2717 0.7951 0.2353 0.7802 0.1979 0.7660 0.1596 0.7525 0.1204 0.7397 0.0805 0.7277 0.0401 0.7167 -0.0002 0.7067 -0.0401 0.6980 -0.0787 0.6906 -0.1152 0.6846 -0.1487 0.6805 -0.1783 0.6783 -0.2033 0.6784 -0.2232 0.6811 -0.2381 0.6874 -0.2487 0.6983 -0.2558 0.7127 -0.2604 0.7787 -0.2632 0.0627 -0.2647 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 41.000 0.389 0.716 -0.148 0.177 1.000 0.0000 -0.6140 Cpi Cpv ----------------- 0.0787 -0.2638 0.1611 -0.2638 0.7002 -0.2638 0.6855 -0.2638 0.6677 -0.2638 0.6509 -0.2638 0.6330 -0.2638 0.6140 -0.2639 0.5938 -0.2640 0.5718 -0.2641 0.5480 -0.2643 0.5219 -0.2646 0.4932 -0.2649 0.4617 -0.2653 0.4269 -0.2658 0.3884 -0.2664 0.3458 -0.2671 0.2986 -0.2680 0.2463 -0.2690 0.1884 -0.2702 0.1242 -0.2715 0.0530 -0.2730 -0.0259 -0.2747 -0.1134 -0.2766 -0.2103 -0.2787 -0.3176 -0.2811 -0.4364 -0.2837 -0.5679 -0.2866 -0.7135 -0.2899 -0.8747 -0.2934 -1.0533 -0.2974 -1.2513 -0.3017 -1.4712 -0.3066 -1.7159 -0.3120 -1.9891 -0.3181 -2.2953 -0.3249 -2.6406 -0.3326 -3.0326 -0.3416 -3.4820 -0.3522 -4.0031 -0.3651 -4.6162 -0.3817 -5.3508 -0.4064 -6.2499 -0.4419 -7.3802 -0.4443 -8.8476 -0.4471 -10.8286 -0.4506 -13.6345 -0.4546 -17.8495 -0.4591 -24.6618 -0.4637 -36.5886 -0.4679 -59.1397 -0.4733 -91.8258 -0.5007 -76.1064 -0.6140 -35.5236 -0.2539 -16.4747 0.3945 -8.0751 0.7515 -4.0227 0.9202 -1.8992 0.9857 -0.7130 0.9998 -0.0196 0.9855 0.3978 0.9569 0.6530 0.9203 0.8093 0.8808 0.9036 0.8398 0.9581 0.7993 0.9868 0.7596 0.9985 0.7212 0.9992 0.6842 0.9927 0.6484 0.9815 0.6137 0.9675 0.5799 0.9516 0.5468 0.9348 0.5141 0.9175 0.4815 0.9001 0.4489 0.8828 0.4161 0.8658 0.3827 0.8491 0.3487 0.8328 0.3139 0.8169 0.2782 0.8016 0.2416 0.7868 0.2039 0.7726 0.1652 0.7591 0.1257 0.7462 0.0854 0.7343 0.0447 0.7232 0.0040 0.7132 -0.0362 0.7044 -0.0752 0.6969 -0.1122 0.6909 -0.1461 0.6866 -0.1761 0.6843 -0.2014 0.6843 -0.2216 0.6868 -0.2368 0.6930 -0.2475 0.7036 -0.2547 0.7177 -0.2594 0.7825 -0.2622 0.0787 -0.2638 Reynolds = 10000 Mach = 0 NCrit = 9.0 Alpha,Cd,Cl,Cm,XTr1,XTr2,TEHMom,Cpmn 41.500 0.395 0.717 -0.149 0.171 1.000 0.0000 -0.6160 Cpi Cpv ----------------- 0.0947 -0.2629 0.1757 -0.2629 0.7054 -0.2629 0.6908 -0.2629 0.6733 -0.2629 0.6567 -0.2629 0.6390 -0.2630 0.6202 -0.2630 0.6002 -0.2631 0.5784 -0.2633 0.5547 -0.2634 0.5288 -0.2637 0.5003 -0.2640 0.4689 -0.2644 0.4342 -0.2649 0.3959 -0.2655 0.3534 -0.2662 0.3064 -0.2670 0.2542 -0.2680 0.1963 -0.2691 0.1322 -0.2704 0.0611 -0.2719 -0.0179 -0.2736 -0.1053 -0.2755 -0.2023 -0.2776 -0.3098 -0.2799 -0.4289 -0.2825 -0.5608 -0.2854 -0.7069 -0.2886 -0.8688 -0.2921 -1.0483 -0.2960 -1.2475 -0.3004 -1.4688 -0.3052 -1.7152 -0.3106 -1.9906 -0.3167 -2.2994 -0.3235 -2.6479 -0.3314 -3.0440 -0.3405 -3.4983 -0.3512 -4.0256 -0.3642 -4.6465 -0.3809 -5.3908 -0.4046 -6.3026 -0.4524 -7.4494 -0.4548 -8.9395 -0.4577 -10.9522 -0.4611 -13.8049 -0.4651 -18.0931 -0.4696 -25.0289 -0.4741 -37.1825 -0.4780 -60.1890 -0.4829 -93.6241 -0.5077 -77.7693 -0.6160 -36.4006 -0.2876 -16.9407 0.3640 -8.3449 0.7328 -4.1901 0.9091 -2.0083 0.9821 -0.7865 1.0000 -0.0702 0.9890 0.3627 0.9618 0.6287 0.9274 0.7928 0.8882 0.8927 0.8484 0.9513 0.8081 0.9831 0.7688 0.9973 0.7305 0.9998 0.6935 0.9947 0.6576 0.9846 0.6228 0.9713 0.5889 0.9561 0.5556 0.9398 0.5226 0.9229 0.4899 0.9058 0.4571 0.8888 0.4239 0.8719 0.3903 0.8553 0.3561 0.8391 0.3210 0.8234 0.2850 0.8081 0.2481 0.7933 0.2101 0.7791 0.1711 0.7656 0.1312 0.7528 0.0906 0.7408 0.0495 0.7297 0.0084 0.7196 -0.0322 0.7108 -0.0717 0.7032 -0.1090 0.6971 -0.1434 0.6928 -0.1738 0.6904 -0.1995 0.6902 -0.2200 0.6926 -0.2354 0.6985 -0.2463 0.7088 -0.2537 0.7226 -0.2585 0.7863 -0.2613 0.0947 -0.2629