XFOIL         Version 6.94
  
 Calculated polar for: AH 79-K-132/20                                  
  
 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   0.3079   0.01535   0.01039  -0.0589  0.7381  0.9451
   0.500   0.4496   0.01548   0.01038  -0.0758  0.7331  0.9635
   1.000   0.5266   0.01508   0.00989  -0.0804  0.7280  0.9711
   1.500   0.5876   0.01483   0.00960  -0.0820  0.7205  0.9776
   2.000   0.6591   0.01420   0.00892  -0.0855  0.7160  0.9815
   2.500   0.7211   0.01388   0.00864  -0.0873  0.7074  0.9873
   3.000   0.7909   0.01335   0.00815  -0.0906  0.7001  0.9914
   3.500   0.8587   0.01260   0.00740  -0.0932  0.6934  0.9955
   4.000   0.9249   0.01201   0.00689  -0.0957  0.6828  0.9995
   4.500   0.9701   0.01164   0.00662  -0.0939  0.6690  1.0000
   5.000   1.0129   0.01129   0.00636  -0.0914  0.6527  1.0000
   5.500   1.0541   0.01091   0.00601  -0.0885  0.6280  1.0000
   6.000   1.0893   0.01094   0.00605  -0.0846  0.5982  1.0000
   6.500   1.1191   0.01121   0.00629  -0.0798  0.5658  1.0000
   7.000   1.1412   0.01165   0.00673  -0.0736  0.5323  1.0000
   7.500   1.1496   0.01228   0.00725  -0.0649  0.4891  1.0000
   8.000   1.1574   0.01335   0.00809  -0.0568  0.4287  1.0000
   8.500   1.1512   0.01515   0.00953  -0.0474  0.3552  1.0000
   9.000   1.1427   0.01829   0.01224  -0.0407  0.2700  1.0000
   9.500   1.1359   0.02191   0.01534  -0.0350  0.1807  1.0000
  10.000   1.1146   0.02681   0.01940  -0.0284  0.0612  1.0000
  10.500   1.1082   0.03118   0.02347  -0.0236  0.0211  1.0000
  11.000   1.1128   0.03502   0.02747  -0.0201  0.0155  1.0000
  11.500   1.1202   0.03884   0.03151  -0.0174  0.0140  1.0000
  12.000   1.1268   0.04300   0.03584  -0.0151  0.0133  1.0000
  12.500   1.1290   0.04785   0.04083  -0.0130  0.0123  1.0000
  13.000   1.1334   0.05262   0.04573  -0.0103  0.0118  1.0000
  13.500   1.1542   0.05611   0.04940  -0.0079  0.0116  1.0000
  14.000   1.1739   0.06003   0.05364  -0.0064  0.0112  1.0000
  14.500   1.1871   0.06488   0.05883  -0.0052  0.0109  1.0000
  15.000   1.1908   0.07114   0.06553  -0.0044  0.0106  1.0000
  15.500   1.1835   0.07918   0.07402  -0.0044  0.0109  1.0000
  16.000   1.1650   0.08894   0.08423  -0.0059  0.0111  1.0000
  16.500   1.1388   0.10037   0.09605  -0.0091  0.0114  1.0000
  17.000   1.1253   0.11039   0.10636  -0.0125  0.0119  1.0000