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I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 961 (isa961-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.89 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa961-il-1000000-n5.txt
Download as CSV file: xf-isa961-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 961                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5208   0.06060   0.05886  -0.0610   0.9875   0.0042
 -10.500  -0.5466   0.02593   0.02313  -0.0974   0.9578   0.0041
 -10.250  -0.5234   0.02239   0.01923  -0.0993   0.9465   0.0042
 -10.000  -0.4993   0.02038   0.01694  -0.1000   0.9351   0.0042
  -9.750  -0.4753   0.01896   0.01529  -0.1001   0.9240   0.0043
  -9.500  -0.4525   0.01732   0.01338  -0.0999   0.9147   0.0044
  -9.250  -0.4289   0.01596   0.01178  -0.0997   0.9068   0.0046
  -9.000  -0.4037   0.01507   0.01075  -0.0995   0.9000   0.0047
  -8.750  -0.3778   0.01439   0.00993  -0.0993   0.8934   0.0048
  -8.500  -0.3515   0.01379   0.00921  -0.0991   0.8876   0.0050
  -8.250  -0.3250   0.01320   0.00851  -0.0988   0.8815   0.0051
  -8.000  -0.2984   0.01267   0.00786  -0.0986   0.8756   0.0053
  -7.750  -0.2718   0.01218   0.00725  -0.0983   0.8663   0.0055
  -7.500  -0.2451   0.01171   0.00665  -0.0980   0.8564   0.0057
  -7.250  -0.2182   0.01129   0.00611  -0.0977   0.8474   0.0060
  -7.000  -0.1908   0.01092   0.00565  -0.0975   0.8384   0.0062
  -6.750  -0.1635   0.01064   0.00527  -0.0973   0.8279   0.0064
  -6.500  -0.1368   0.01013   0.00464  -0.0970   0.8141   0.0071
  -6.250  -0.1098   0.00986   0.00425  -0.0966   0.7960   0.0075
  -6.000  -0.0831   0.00965   0.00390  -0.0962   0.7717   0.0079
  -5.750  -0.0563   0.00948   0.00357  -0.0958   0.7449   0.0084
  -5.500  -0.0293   0.00933   0.00328  -0.0955   0.7213   0.0090
  -5.250  -0.0022   0.00919   0.00301  -0.0952   0.6987   0.0095
  -5.000   0.0250   0.00899   0.00269  -0.0949   0.6783   0.0108
  -4.750   0.0524   0.00887   0.00247  -0.0947   0.6571   0.0123
  -4.500   0.0796   0.00883   0.00228  -0.0945   0.6325   0.0134
  -4.250   0.1066   0.00877   0.00209  -0.0942   0.6031   0.0169
  -4.000   0.1329   0.00859   0.00188  -0.0939   0.5686   0.0408
  -3.750   0.1592   0.00870   0.00188  -0.0936   0.5221   0.0568
  -3.500   0.1848   0.00897   0.00191  -0.0931   0.4589   0.0623
  -3.250   0.2111   0.00921   0.00193  -0.0928   0.4101   0.0652
  -3.000   0.2381   0.00937   0.00194  -0.0926   0.3791   0.0667
  -2.750   0.2653   0.00943   0.00189  -0.0924   0.3545   0.0688
  -2.500   0.2921   0.00953   0.00186  -0.0922   0.3224   0.0728
  -2.250   0.3182   0.00976   0.00188  -0.0919   0.2753   0.0748
  -2.000   0.3450   0.00990   0.00188  -0.0917   0.2471   0.0759
  -1.750   0.3717   0.01005   0.00190  -0.0915   0.2213   0.0772
  -1.500   0.3986   0.01020   0.00192  -0.0913   0.1982   0.0782
  -1.250   0.4235   0.01059   0.00204  -0.0908   0.1296   0.0789
  -0.750   0.4782   0.01076   0.00211  -0.0906   0.1132   0.0807
  -0.500   0.5057   0.01081   0.00214  -0.0905   0.1106   0.0836
  -0.250   0.5331   0.01086   0.00218  -0.0904   0.1086   0.0876
   0.000   0.5605   0.01092   0.00224  -0.0903   0.1065   0.0926
   0.250   0.5877   0.01093   0.00234  -0.0903   0.1039   0.1289
   0.500   0.6150   0.01100   0.00243  -0.0902   0.1016   0.1441
   0.750   0.6423   0.01107   0.00251  -0.0901   0.1001   0.1532
   1.000   0.6697   0.01113   0.00259  -0.0901   0.0996   0.1617
   1.250   0.6970   0.01120   0.00268  -0.0900   0.0990   0.1699
   1.750   0.7513   0.01133   0.00287  -0.0899   0.0962   0.1992
   2.000   0.7782   0.01137   0.00301  -0.0899   0.0935   0.2460
   2.250   0.8045   0.01142   0.00316  -0.0898   0.0888   0.3157
   2.750   0.8571   0.01050   0.00364  -0.0899   0.0584   1.0000
   3.000   0.8831   0.01072   0.00382  -0.0896   0.0541   1.0000
   3.250   0.9093   0.01091   0.00399  -0.0894   0.0515   1.0000
   3.500   0.9354   0.01109   0.00416  -0.0892   0.0506   1.0000
   3.750   0.9615   0.01127   0.00434  -0.0890   0.0501   1.0000
   4.000   0.9875   0.01147   0.00454  -0.0888   0.0496   1.0000
   4.250   1.0133   0.01167   0.00475  -0.0885   0.0491   1.0000
   4.500   1.0390   0.01188   0.00496  -0.0883   0.0486   1.0000
   4.750   1.0645   0.01210   0.00519  -0.0880   0.0481   1.0000
   5.000   1.0898   0.01234   0.00544  -0.0877   0.0470   1.0000
   5.250   1.1146   0.01262   0.00572  -0.0873   0.0454   1.0000
   5.500   1.1389   0.01294   0.00604  -0.0869   0.0431   1.0000
   5.750   1.1634   0.01322   0.00633  -0.0865   0.0418   1.0000
   6.000   1.1885   0.01342   0.00655  -0.0862   0.0410   1.0000
   6.250   1.2133   0.01365   0.00678  -0.0859   0.0395   1.0000
   6.500   1.2373   0.01395   0.00705  -0.0855   0.0363   1.0000
   6.750   1.2594   0.01440   0.00739  -0.0848   0.0210   1.0000
   7.000   1.2806   0.01494   0.00791  -0.0839   0.0122   1.0000
   7.250   1.3026   0.01538   0.00839  -0.0831   0.0100   1.0000
   7.500   1.3243   0.01581   0.00886  -0.0823   0.0084   1.0000
   7.750   1.3460   0.01623   0.00931  -0.0816   0.0074   1.0000
   8.000   1.3666   0.01671   0.00981  -0.0806   0.0065   1.0000
   8.250   1.3870   0.01718   0.01033  -0.0796   0.0059   1.0000
   8.500   1.4072   0.01764   0.01083  -0.0787   0.0055   1.0000
   8.750   1.4264   0.01814   0.01138  -0.0775   0.0051   1.0000
   9.000   1.4442   0.01869   0.01197  -0.0762   0.0047   1.0000
   9.250   1.4590   0.01935   0.01267  -0.0743   0.0042   1.0000
   9.500   1.4739   0.01991   0.01328  -0.0725   0.0040   1.0000
   9.750   1.4884   0.02051   0.01393  -0.0706   0.0038   1.0000
  10.000   1.5019   0.02118   0.01466  -0.0687   0.0036   1.0000
  10.250   1.5149   0.02191   0.01545  -0.0668   0.0034   1.0000
  10.500   1.5272   0.02270   0.01629  -0.0650   0.0033   1.0000
  10.750   1.5386   0.02358   0.01722  -0.0631   0.0031   1.0000
  11.000   1.5484   0.02459   0.01832  -0.0612   0.0030   1.0000
  11.250   1.5557   0.02583   0.01964  -0.0591   0.0028   1.0000
  11.500   1.5628   0.02714   0.02104  -0.0572   0.0027   1.0000
  11.750   1.5709   0.02841   0.02240  -0.0555   0.0027   1.0000
  12.000   1.5779   0.02983   0.02390  -0.0540   0.0026   1.0000
  12.250   1.5835   0.03141   0.02557  -0.0524   0.0025   1.0000
  12.500   1.5882   0.03314   0.02740  -0.0510   0.0025   1.0000
  12.750   1.5919   0.03505   0.02940  -0.0497   0.0024   1.0000
  13.000   1.5942   0.03716   0.03161  -0.0486   0.0023   1.0000
  13.250   1.5961   0.03941   0.03396  -0.0477   0.0022   1.0000
  13.500   1.5967   0.04190   0.03655  -0.0470   0.0022   1.0000
  13.750   1.5962   0.04459   0.03934  -0.0464   0.0021   1.0000
  14.000   1.5949   0.04750   0.04235  -0.0461   0.0021   1.0000
  14.250   1.5924   0.05069   0.04564  -0.0460   0.0020   1.0000
  14.500   1.5880   0.05425   0.04931  -0.0462   0.0020   1.0000
  14.750   1.5823   0.05813   0.05330  -0.0466   0.0019   1.0000
  15.000   1.5743   0.06251   0.05779  -0.0474   0.0019   1.0000
  15.250   1.5643   0.06737   0.06277  -0.0485   0.0019   1.0000
  15.500   1.5521   0.07267   0.06819  -0.0498   0.0018   1.0000
  15.750   1.5381   0.07844   0.07409  -0.0515   0.0018   1.0000
  16.000   1.5222   0.08467   0.08045  -0.0534   0.0018   1.0000
  16.250   1.5049   0.09119   0.08710  -0.0556   0.0018   1.0000
  16.500   1.4867   0.09797   0.09401  -0.0579   0.0018   1.0000
  16.750   1.4686   0.10485   0.10101  -0.0603   0.0018   1.0000
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