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I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 962 (isa962-il)
Reynolds number: 200,000
Max Cl/Cd: 77.06 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa962-il-200000.txt
Download as CSV file: xf-isa962-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 962                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3315   0.09817   0.09467  -0.0332   1.0000   0.0524
  -9.000  -0.3556   0.09771   0.09433  -0.0303   1.0000   0.0525
  -8.750  -0.3747   0.09662   0.09330  -0.0294   1.0000   0.0526
  -8.500  -0.3826   0.09379   0.09054  -0.0272   1.0000   0.0529
  -8.250  -0.3776   0.09096   0.08775  -0.0232   0.9996   0.0533
  -8.000  -0.3555   0.08751   0.08429  -0.0237   0.9969   0.0542
  -7.750  -0.3296   0.08374   0.08051  -0.0282   0.9932   0.0555
  -7.500  -0.3030   0.07965   0.07639  -0.0348   0.9874   0.0579
  -7.250  -0.2596   0.07145   0.06801  -0.0568   0.9781   0.0621
  -7.000  -0.2378   0.06843   0.06502  -0.0567   0.9744   0.0630
  -6.750  -0.2080   0.06524   0.06182  -0.0599   0.9713   0.0646
  -6.500  -0.1793   0.06179   0.05831  -0.0648   0.9642   0.0673
  -6.250  -0.1297   0.05472   0.05095  -0.0796   0.9591   0.0729
  -6.000  -0.1012   0.05219   0.04845  -0.0813   0.9552   0.0744
  -5.750  -0.0520   0.04763   0.04335  -0.0919   0.9479   0.0837
  -5.500  -0.0232   0.04429   0.04018  -0.0935   0.9447   0.0852
  -5.250   0.0050   0.04225   0.03815  -0.0948   0.9377   0.0878
  -5.000   0.0469   0.03840   0.03382  -0.1006   0.9309   0.0976
  -4.750   0.0742   0.03610   0.03159  -0.1015   0.9238   0.0996
  -4.500   0.1022   0.03430   0.02973  -0.1022   0.9154   0.1035
  -4.250   0.1331   0.03173   0.02680  -0.1039   0.9067   0.1132
  -4.000   0.1588   0.03007   0.02513  -0.1039   0.8981   0.1164
  -3.750   0.1864   0.02846   0.02316  -0.1043   0.8881   0.1282
  -3.500   0.2227   0.02146   0.01495  -0.1042   0.8810   0.0741
  -3.250   0.2494   0.01973   0.01290  -0.1033   0.8706   0.0684
  -3.000   0.2779   0.01807   0.01086  -0.1027   0.8630   0.0655
  -2.750   0.3040   0.01698   0.00951  -0.1017   0.8515   0.0644
  -2.500   0.3311   0.01617   0.00856  -0.1010   0.8423   0.0646
  -2.250   0.3580   0.01552   0.00783  -0.1002   0.8324   0.0656
  -2.000   0.3845   0.01506   0.00733  -0.0995   0.8216   0.0681
  -1.750   0.4122   0.01453   0.00671  -0.0989   0.8133   0.0701
  -1.500   0.4387   0.01409   0.00626  -0.0982   0.8022   0.0716
  -1.250   0.4655   0.01353   0.00575  -0.0976   0.7925   0.0746
  -1.000   0.4926   0.01319   0.00540  -0.0970   0.7818   0.0794
  -0.750   0.5192   0.01288   0.00512  -0.0963   0.7690   0.0877
  -0.500   0.5462   0.01255   0.00484  -0.0957   0.7568   0.1122
  -0.250   0.5705   0.01141   0.00468  -0.0951   0.7459   0.4111
   0.000   0.6072   0.01011   0.00454  -0.0963   0.7336   1.0000
   0.250   0.6338   0.01019   0.00447  -0.0957   0.7204   1.0000
   0.500   0.6605   0.01028   0.00442  -0.0951   0.7068   1.0000
   0.750   0.6870   0.01038   0.00437  -0.0945   0.6923   1.0000
   1.000   0.7134   0.01049   0.00436  -0.0939   0.6777   1.0000
   1.250   0.7398   0.01061   0.00436  -0.0934   0.6629   1.0000
   1.500   0.7659   0.01074   0.00438  -0.0928   0.6467   1.0000
   1.750   0.7918   0.01088   0.00443  -0.0921   0.6287   1.0000
   2.000   0.8173   0.01102   0.00448  -0.0915   0.6082   1.0000
   2.250   0.8426   0.01119   0.00453  -0.0908   0.5866   1.0000
   2.500   0.8676   0.01140   0.00461  -0.0900   0.5638   1.0000
   2.750   0.8922   0.01162   0.00472  -0.0893   0.5371   1.0000
   3.000   0.9163   0.01189   0.00485  -0.0885   0.5087   1.0000
   3.250   0.9400   0.01221   0.00502  -0.0876   0.4797   1.0000
   3.500   0.9635   0.01258   0.00523  -0.0868   0.4522   1.0000
   3.750   0.9869   0.01297   0.00548  -0.0860   0.4269   1.0000
   4.000   1.0099   0.01340   0.00576  -0.0852   0.4044   1.0000
   4.250   1.0329   0.01385   0.00608  -0.0844   0.3843   1.0000
   4.500   1.0558   0.01430   0.00643  -0.0836   0.3652   1.0000
   4.750   1.0784   0.01478   0.00683  -0.0828   0.3464   1.0000
   5.000   1.1006   0.01529   0.00724  -0.0819   0.3272   1.0000
   5.250   1.1220   0.01584   0.00768  -0.0809   0.3066   1.0000
   5.500   1.1433   0.01636   0.00813  -0.0800   0.2841   1.0000
   5.750   1.1645   0.01687   0.00858  -0.0790   0.2610   1.0000
   6.000   1.1850   0.01743   0.00904  -0.0779   0.2418   1.0000
   6.250   1.2055   0.01801   0.00952  -0.0769   0.2263   1.0000
   6.500   1.2261   0.01859   0.01004  -0.0759   0.2139   1.0000
   6.750   1.2461   0.01922   0.01065  -0.0748   0.2045   1.0000
   7.000   1.2648   0.01995   0.01128  -0.0736   0.1963   1.0000
   7.250   1.2849   0.02060   0.01195  -0.0725   0.1889   1.0000
   7.500   1.3032   0.02141   0.01269  -0.0713   0.1822   1.0000
   7.750   1.3228   0.02218   0.01348  -0.0702   0.1764   1.0000
   8.000   1.3421   0.02292   0.01425  -0.0691   0.1708   1.0000
   8.250   1.3622   0.02408   0.01525  -0.0683   0.1653   1.0000
   8.500   1.3811   0.02471   0.01605  -0.0671   0.1608   1.0000
   8.750   1.3996   0.02547   0.01686  -0.0660   0.1558   1.0000
   9.000   1.4213   0.02673   0.01797  -0.0656   0.1502   1.0000
   9.250   1.4358   0.02728   0.01873  -0.0638   0.1461   1.0000
   9.500   1.4509   0.02796   0.01951  -0.0622   0.1415   1.0000
   9.750   1.4671   0.02885   0.02036  -0.0609   0.1374   1.0000
  10.000   1.4836   0.02984   0.02143  -0.0597   0.1337   1.0000
  10.250   1.4952   0.03057   0.02232  -0.0576   0.1304   1.0000
  10.500   1.5072   0.03133   0.02318  -0.0558   0.1270   1.0000
  10.750   1.5196   0.03218   0.02404  -0.0541   0.1238   1.0000
  11.000   1.5346   0.03330   0.02519  -0.0530   0.1206   1.0000
  11.250   1.5425   0.03421   0.02632  -0.0509   0.1180   1.0000
  11.500   1.5516   0.03518   0.02742  -0.0491   0.1151   1.0000
  11.750   1.5606   0.03616   0.02849  -0.0476   0.1124   1.0000
  12.000   1.5698   0.03726   0.02959  -0.0462   0.1097   1.0000
  12.250   1.5771   0.03857   0.03105  -0.0447   0.1070   1.0000
  12.500   1.5824   0.03992   0.03260  -0.0432   0.1044   1.0000
  12.750   1.5882   0.04129   0.03411  -0.0419   0.1018   1.0000
  13.000   1.5937   0.04273   0.03565  -0.0408   0.0994   1.0000
  13.250   1.5991   0.04431   0.03722  -0.0398   0.0968   1.0000
  13.500   1.6009   0.04625   0.03940  -0.0390   0.0941   1.0000
  13.750   1.6026   0.04827   0.04162  -0.0384   0.0909   1.0000
  14.000   1.6033   0.05047   0.04392  -0.0381   0.0876   1.0000
  14.250   1.6025   0.05300   0.04650  -0.0379   0.0843   1.0000
  14.500   1.6028   0.05566   0.04944  -0.0380   0.0803   1.0000
  14.750   1.6001   0.05876   0.05263  -0.0385   0.0761   1.0000
  15.000   1.5971   0.06213   0.05617  -0.0390   0.0713   1.0000
  15.250   1.5910   0.06610   0.06025  -0.0400   0.0659   1.0000
  15.500   1.5838   0.07037   0.06467  -0.0410   0.0595   1.0000
  15.750   1.5710   0.07556   0.06995  -0.0424   0.0543   1.0000
  16.000   1.5562   0.08125   0.07574  -0.0441   0.0495   1.0000
  16.250   1.5397   0.08733   0.08194  -0.0460   0.0458   1.0000
  16.500   1.5211   0.09398   0.08870  -0.0484   0.0431   1.0000
  16.750   1.5004   0.10119   0.09601  -0.0513   0.0416   1.0000
  17.000   1.4821   0.10817   0.10313  -0.0542   0.0398   1.0000
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