XFOIL         Version 6.94
  
 Calculated polar for: HAWKER TEMPEST 96.77% SEMISPAN A                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.1354   0.00680   0.00284  -0.0262  0.8626  0.9447
   0.500   0.2082   0.00698   0.00293  -0.0295  0.8403  0.9545
   1.000   0.2865   0.00712   0.00298  -0.0342  0.8131  0.9592
   1.500   0.3547   0.00726   0.00306  -0.0368  0.7841  0.9674
   2.000   0.4225   0.00741   0.00312  -0.0394  0.7472  0.9750
   2.500   0.4924   0.00754   0.00316  -0.0425  0.7012  0.9813
   3.000   0.5579   0.00774   0.00324  -0.0447  0.6452  0.9886
   3.500   0.6225   0.00815   0.00333  -0.0470  0.5480  0.9956
   4.000   0.6752   0.00906   0.00354  -0.0473  0.3743  1.0000
   4.500   0.7033   0.01041   0.00413  -0.0426  0.2046  1.0000
   5.000   0.7292   0.01201   0.00498  -0.0376  0.0582  1.0000
   5.500   0.7585   0.01333   0.00620  -0.0326  0.0283  1.0000
   6.000   0.7881   0.01451   0.00748  -0.0277  0.0222  1.0000
   6.500   0.8162   0.01580   0.00891  -0.0224  0.0191  1.0000
   7.000   0.8425   0.01733   0.01054  -0.0169  0.0168  1.0000
   7.500   0.8686   0.01955   0.01295  -0.0115  0.0149  1.0000
   8.000   0.9010   0.02189   0.01553  -0.0072  0.0137  1.0000
   8.500   0.9334   0.02468   0.01859  -0.0032  0.0128  1.0000
   9.000   0.9597   0.02894   0.02336   0.0016  0.0126  1.0000
   9.500   0.9533   0.03790   0.03336   0.0110  0.0144  1.0000