XFOIL         Version 6.94
  
 Calculated polar for: AH21 7% version (Andrew Hollom)                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.2499   0.01096   0.00662  -0.0691  0.9292  1.0000
   0.500   0.2979   0.01069   0.00629  -0.0675  0.9126  1.0000
   1.000   0.3844   0.01006   0.00569  -0.0733  0.9042  1.0000
   1.500   0.4900   0.00912   0.00476  -0.0827  0.8983  1.0000
   2.000   0.5321   0.00863   0.00429  -0.0790  0.8735  1.0000
   2.500   0.5965   0.00808   0.00376  -0.0799  0.8437  1.0000
   3.000   0.6720   0.00770   0.00330  -0.0831  0.7919  1.0000
   3.500   0.7263   0.00803   0.00315  -0.0820  0.6678  1.0000
   4.000   0.7504   0.00929   0.00351  -0.0752  0.4910  1.0000
   4.500   0.7720   0.01109   0.00441  -0.0688  0.2865  1.0000
   5.000   0.8091   0.01244   0.00517  -0.0657  0.1744  1.0000
   5.500   0.8495   0.01371   0.00607  -0.0631  0.1073  1.0000
   6.000   0.8908   0.01498   0.00724  -0.0606  0.0759  1.0000
   6.500   0.9283   0.01676   0.00898  -0.0574  0.0566  1.0000
   7.000   0.9759   0.01726   0.00950  -0.0562  0.0470  1.0000
   7.500   1.0130   0.01912   0.01136  -0.0533  0.0363  1.0000
   8.000   1.0581   0.01978   0.01211  -0.0517  0.0327  1.0000
   8.500   1.0970   0.02375   0.01680  -0.0487  0.0341  1.0000
   9.000   1.1343   0.02370   0.01678  -0.0460  0.0267  1.0000
  10.000   1.1929   0.03034   0.02411  -0.0385  0.0181  1.0000
  10.500   1.2155   0.03306   0.02719  -0.0340  0.0162  1.0000
  11.000   1.2349   0.03476   0.02908  -0.0293  0.0140  1.0000
  11.500   1.2538   0.03558   0.02991  -0.0251  0.0118  1.0000
  12.000   1.2296   0.04223   0.03713  -0.0176  0.0099  1.0000
  12.500   1.1907   0.05064   0.04616  -0.0122  0.0092  1.0000
  13.000   1.1741   0.05694   0.05283  -0.0108  0.0090  1.0000