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I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 961 (isa961-il)
Reynolds number: 1,000,000
Max Cl/Cd: 90.63 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa961-il-1000000.txt
Download as CSV file: xf-isa961-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2692   0.09930   0.09778  -0.0345   1.0000   0.0131
 -11.000  -0.2706   0.09523   0.09372  -0.0351   1.0000   0.0131
 -10.750  -0.2789   0.09017   0.08869  -0.0355   1.0000   0.0135
 -10.500  -0.2774   0.08752   0.08606  -0.0353   1.0000   0.0137
 -10.250  -0.2771   0.08497   0.08352  -0.0349   1.0000   0.0139
 -10.000  -0.2748   0.08190   0.08048  -0.0354   0.9995   0.0142
  -9.750  -0.2665   0.07760   0.07618  -0.0383   0.9978   0.0145
  -9.500  -0.4857   0.02488   0.02207  -0.0901   0.9848   0.0089
  -9.250  -0.4600   0.02163   0.01842  -0.0920   0.9807   0.0090
  -9.000  -0.4332   0.01947   0.01596  -0.0931   0.9756   0.0091
  -8.750  -0.4034   0.01798   0.01423  -0.0942   0.9719   0.0094
  -8.500  -0.3759   0.01712   0.01321  -0.0944   0.9648   0.0096
  -8.250  -0.3474   0.01584   0.01170  -0.0949   0.9588   0.0099
  -8.000  -0.3237   0.01380   0.00939  -0.0947   0.9502   0.0104
  -7.750  -0.2963   0.01299   0.00847  -0.0947   0.9428   0.0108
  -7.500  -0.2699   0.01239   0.00776  -0.0943   0.9332   0.0112
  -7.250  -0.2436   0.01183   0.00708  -0.0938   0.9226   0.0116
  -7.000  -0.2175   0.01135   0.00647  -0.0933   0.9116   0.0120
  -6.750  -0.1911   0.01092   0.00591  -0.0928   0.9013   0.0125
  -6.500  -0.1643   0.01054   0.00544  -0.0924   0.8919   0.0129
  -6.250  -0.1376   0.01009   0.00486  -0.0919   0.8830   0.0133
  -6.000  -0.1112   0.00946   0.00412  -0.0915   0.8731   0.0144
  -5.750  -0.0839   0.00914   0.00373  -0.0912   0.8638   0.0156
  -5.500  -0.0565   0.00889   0.00339  -0.0908   0.8548   0.0167
  -5.250  -0.0289   0.00858   0.00301  -0.0906   0.8451   0.0179
  -5.000  -0.0016   0.00827   0.00264  -0.0902   0.8337   0.0206
  -4.750   0.0257   0.00796   0.00229  -0.0899   0.8215   0.0293
  -4.500   0.0531   0.00780   0.00228  -0.0897   0.8087   0.0594
  -4.250   0.0812   0.00791   0.00234  -0.0895   0.7941   0.0649
  -4.000   0.1091   0.00791   0.00227  -0.0893   0.7785   0.0679
  -3.750   0.1365   0.00781   0.00210  -0.0890   0.7604   0.0715
  -3.500   0.1639   0.00780   0.00201  -0.0888   0.7402   0.0743
  -3.250   0.1914   0.00782   0.00194  -0.0886   0.7208   0.0771
  -3.000   0.2190   0.00784   0.00187  -0.0884   0.7026   0.0787
  -2.750   0.2465   0.00779   0.00174  -0.0882   0.6837   0.0809
  -2.500   0.2737   0.00772   0.00159  -0.0879   0.6631   0.0853
  -2.250   0.3011   0.00771   0.00149  -0.0877   0.6416   0.0874
  -2.000   0.3283   0.00775   0.00142  -0.0875   0.6167   0.0894
  -1.750   0.3549   0.00786   0.00137  -0.0872   0.5797   0.0912
  -1.500   0.3807   0.00807   0.00136  -0.0867   0.5285   0.0929
  -1.250   0.4065   0.00828   0.00137  -0.0863   0.4779   0.0978
  -1.000   0.4327   0.00845   0.00141  -0.0860   0.4389   0.1060
  -0.750   0.4592   0.00856   0.00149  -0.0858   0.4073   0.1377
  -0.500   0.4858   0.00870   0.00155  -0.0856   0.3785   0.1564
  -0.250   0.5121   0.00891   0.00162  -0.0853   0.3422   0.1693
   0.000   0.5382   0.00913   0.00170  -0.0851   0.3055   0.1812
   0.250   0.5641   0.00936   0.00181  -0.0848   0.2696   0.1975
   0.500   0.5901   0.00953   0.00194  -0.0845   0.2410   0.2325
   0.750   0.6163   0.00957   0.00207  -0.0844   0.2209   0.3067
   1.000   0.6316   0.00829   0.00229  -0.0822   0.2014   0.9028
   1.500   0.6970   0.00908   0.00272  -0.0848   0.1181   1.0000
   1.750   0.7236   0.00925   0.00285  -0.0845   0.1153   1.0000
   2.000   0.7500   0.00942   0.00297  -0.0843   0.1127   1.0000
   2.250   0.7764   0.00960   0.00311  -0.0840   0.1095   1.0000
   2.500   0.8028   0.00978   0.00326  -0.0838   0.1065   1.0000
   2.750   0.8296   0.00991   0.00338  -0.0836   0.1051   1.0000
   3.000   0.8564   0.01004   0.00349  -0.0835   0.1036   1.0000
   3.250   0.8829   0.01019   0.00362  -0.0833   0.1009   1.0000
   3.500   0.9089   0.01040   0.00379  -0.0831   0.0965   1.0000
   3.750   0.9351   0.01059   0.00395  -0.0828   0.0925   1.0000
   4.000   0.9617   0.01073   0.00407  -0.0827   0.0906   1.0000
   4.250   0.9879   0.01090   0.00423  -0.0825   0.0844   1.0000
   4.500   1.0114   0.01137   0.00452  -0.0819   0.0603   1.0000
   4.750   1.0364   0.01167   0.00479  -0.0815   0.0571   1.0000
   5.000   1.0617   0.01192   0.00504  -0.0812   0.0546   1.0000
   5.250   1.0870   0.01217   0.00530  -0.0809   0.0532   1.0000
   5.500   1.1122   0.01242   0.00557  -0.0805   0.0518   1.0000
   5.750   1.1372   0.01267   0.00584  -0.0802   0.0508   1.0000
   6.000   1.1621   0.01293   0.00613  -0.0799   0.0501   1.0000
   6.250   1.1867   0.01321   0.00644  -0.0795   0.0491   1.0000
   6.500   1.2110   0.01350   0.00677  -0.0791   0.0477   1.0000
   6.750   1.2346   0.01386   0.00714  -0.0786   0.0457   1.0000
   7.000   1.2575   0.01427   0.00758  -0.0779   0.0430   1.0000
   7.250   1.2813   0.01457   0.00790  -0.0775   0.0409   1.0000
   7.500   1.3070   0.01467   0.00797  -0.0774   0.0375   1.0000
   7.750   1.3255   0.01542   0.00852  -0.0761   0.0155   1.0000
   8.000   1.3455   0.01603   0.00917  -0.0750   0.0129   1.0000
   8.250   1.3662   0.01656   0.00976  -0.0740   0.0116   1.0000
   8.500   1.3866   0.01706   0.01031  -0.0730   0.0110   1.0000
   8.750   1.4059   0.01763   0.01094  -0.0719   0.0103   1.0000
   9.000   1.4236   0.01829   0.01166  -0.0705   0.0097   1.0000
   9.250   1.4380   0.01916   0.01261  -0.0686   0.0090   1.0000
   9.500   1.4500   0.02005   0.01361  -0.0662   0.0085   1.0000
   9.750   1.4645   0.02064   0.01425  -0.0643   0.0082   1.0000
  10.000   1.4771   0.02135   0.01502  -0.0622   0.0079   1.0000
  10.250   1.4885   0.02216   0.01591  -0.0600   0.0076   1.0000
  10.500   1.4989   0.02306   0.01688  -0.0578   0.0073   1.0000
  10.750   1.5081   0.02407   0.01796  -0.0556   0.0071   1.0000
  11.000   1.5160   0.02522   0.01918  -0.0535   0.0068   1.0000
  11.250   1.5213   0.02660   0.02066  -0.0512   0.0066   1.0000
  11.500   1.5220   0.02841   0.02258  -0.0488   0.0064   1.0000
  11.750   1.5144   0.03102   0.02532  -0.0460   0.0062   1.0000
  12.000   1.5056   0.03394   0.02838  -0.0437   0.0061   1.0000
  12.250   1.5112   0.03573   0.03026  -0.0427   0.0060   1.0000
  12.500   1.5139   0.03789   0.03251  -0.0417   0.0059   1.0000
  12.750   1.5149   0.04031   0.03504  -0.0409   0.0059   1.0000
  13.000   1.5150   0.04297   0.03779  -0.0404   0.0058   1.0000
  13.250   1.5140   0.04589   0.04081  -0.0401   0.0056   1.0000
  13.500   1.5108   0.04917   0.04420  -0.0400   0.0055   1.0000
  13.750   1.5068   0.05269   0.04783  -0.0402   0.0054   1.0000
  14.000   1.5017   0.05654   0.05179  -0.0407   0.0053   1.0000
  14.250   1.4950   0.06074   0.05610  -0.0414   0.0052   1.0000
  14.500   1.4875   0.06523   0.06071  -0.0425   0.0051   1.0000
  14.750   1.4788   0.07006   0.06565  -0.0437   0.0051   1.0000
  15.000   1.4690   0.07517   0.07087  -0.0452   0.0050   1.0000
  15.250   1.4576   0.08060   0.07641  -0.0469   0.0050   1.0000
  15.500   1.4459   0.08620   0.08212  -0.0487   0.0049   1.0000
  15.750   1.4335   0.09195   0.08798  -0.0506   0.0049   1.0000
  16.000   1.4214   0.09769   0.09382  -0.0526   0.0048   1.0000
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