xflr5 v6.58

 Calculated polar for: NACA 0020

 1 1 Reynolds number fixed          Mach number fixed         

 xtrf =   1.000 (top)        1.000 (bottom)
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000

  alpha     CL        CD       CDp       Cm    Top Xtr Bot Xtr   Cpmin    Chinge    XCp    
 ------- -------- --------- --------- -------- ------- ------- -------- --------- ---------
  -4.000  -0.5888   0.02433   0.01616   0.0156  0.9317  0.5102  -1.4698   0.0000   0.0000   0.0000   0.2653
  -2.000  -0.2664   0.02268   0.01506  -0.0000  0.8551  0.6425  -0.9911   0.0000   0.0000   0.0000   0.2389
   0.000  -0.0000   0.02139   0.01407   0.0000  0.7607  0.7607  -0.6821   0.0000   0.0000   0.0000   0.3321
   2.000   0.2664   0.02268   0.01506   0.0000  0.6425  0.8551  -0.9911   0.0000   0.0000   0.0000   0.2389
   4.000   0.5887   0.02432   0.01615  -0.0155  0.5102  0.9317  -1.4698   0.0000   0.0000   0.0000   0.2652
   6.000   0.9072   0.02499   0.01635  -0.0370  0.3808  1.0000  -2.1187   0.0000   0.0000   0.0000   0.2784
   8.000   1.0173   0.02745   0.01840  -0.0209  0.2978  1.0000  -2.5989   0.0000   0.0000   0.0000   0.2555
  10.000   1.0892   0.03191   0.02283   0.0027  0.2339  1.0000  -3.0742   0.0000   0.0000   0.0000   0.2295
  12.000   1.1407   0.03835   0.02938   0.0276  0.1882  1.0000  -3.5466   0.0000   0.0000   0.0000   0.2045