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I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 962 (isa962-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.84 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa962-il-1000000.txt
Download as CSV file: xf-isa962-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3172   0.09673   0.09504  -0.0295   1.0000   0.0222
  -9.750  -0.3140   0.09353   0.09186  -0.0309   1.0000   0.0231
  -9.500  -0.3158   0.08726   0.08561  -0.0384   0.9945   0.0238
  -9.250  -0.3020   0.08226   0.08060  -0.0446   0.9782   0.0238
  -9.000  -0.1994   0.06668   0.06492  -0.0499   0.9161   0.0244
  -8.750  -0.1942   0.06390   0.06210  -0.0506   0.9061   0.0246
  -8.500  -0.1898   0.06103   0.05920  -0.0515   0.8974   0.0248
  -8.250  -0.1861   0.05796   0.05611  -0.0530   0.8892   0.0251
  -8.000  -0.1808   0.05447   0.05259  -0.0557   0.8818   0.0254
  -7.750  -0.1717   0.05042   0.04852  -0.0596   0.8751   0.0259
  -7.500  -0.1605   0.04579   0.04385  -0.0645   0.8682   0.0267
  -7.250  -0.1777   0.05423   0.05211  -0.0743   0.8802   0.0270
  -7.000  -0.1333   0.02726   0.02499  -0.0839   0.8568   0.0285
  -6.750  -0.1137   0.02508   0.02274  -0.0849   0.8495   0.0288
  -6.500  -0.0927   0.02288   0.02046  -0.0861   0.8420   0.0291
  -6.250  -0.0711   0.02027   0.01773  -0.0875   0.8335   0.0296
  -6.000  -0.0475   0.01319   0.00997  -0.0915   0.8284   0.0328
  -5.750  -0.0315   0.00872   0.00509  -0.0926   0.8214   0.0336
  -5.500  -0.0071   0.00794   0.00422  -0.0926   0.8131   0.0339
  -5.250   0.0180   0.00720   0.00339  -0.0926   0.8034   0.0344
  -5.000   0.0432   0.00650   0.00254  -0.0925   0.7931   0.0350
  -4.750   0.0688   0.01324   0.00827  -0.0950   0.8014   0.0301
  -4.500   0.0960   0.01216   0.00695  -0.0947   0.7895   0.0299
  -4.250   0.1235   0.01148   0.00610  -0.0944   0.7768   0.0299
  -4.000   0.1511   0.01093   0.00541  -0.0941   0.7637   0.0300
  -3.750   0.1788   0.01046   0.00483  -0.0939   0.7500   0.0301
  -3.500   0.2065   0.01007   0.00434  -0.0936   0.7354   0.0303
  -3.250   0.2342   0.00974   0.00392  -0.0934   0.7210   0.0306
  -3.000   0.2620   0.00949   0.00359  -0.0932   0.7072   0.0311
  -2.750   0.2898   0.00929   0.00333  -0.0930   0.6943   0.0317
  -2.500   0.3176   0.00910   0.00305  -0.0927   0.6803   0.0321
  -2.250   0.3456   0.00894   0.00283  -0.0926   0.6670   0.0325
  -2.000   0.3738   0.00883   0.00268  -0.0924   0.6553   0.0328
  -1.750   0.4014   0.00847   0.00227  -0.0923   0.6448   0.0336
  -1.500   0.4294   0.00832   0.00208  -0.0922   0.6332   0.0343
  -1.250   0.4576   0.00822   0.00196  -0.0921   0.6216   0.0352
  -1.000   0.4857   0.00816   0.00186  -0.0920   0.6097   0.0361
  -0.750   0.5136   0.00812   0.00178  -0.0918   0.5966   0.0372
  -0.500   0.5415   0.00813   0.00173  -0.0917   0.5812   0.0384
  -0.250   0.5693   0.00808   0.00163  -0.0916   0.5648   0.0413
   0.000   0.5971   0.00810   0.00160  -0.0915   0.5488   0.0440
   0.250   0.6249   0.00810   0.00157  -0.0913   0.5310   0.0526
   0.500   0.6521   0.00801   0.00162  -0.0912   0.5101   0.1251
   0.750   0.6787   0.00796   0.00171  -0.0911   0.4834   0.2213
   1.000   0.7045   0.00792   0.00185  -0.0909   0.4466   0.3657
   1.250   0.7324   0.00688   0.00209  -0.0913   0.3978   1.0000
   1.500   0.7580   0.00721   0.00223  -0.0909   0.3648   1.0000
   1.750   0.7845   0.00745   0.00234  -0.0906   0.3465   1.0000
   2.000   0.8112   0.00765   0.00246  -0.0904   0.3334   1.0000
   2.500   0.8650   0.00801   0.00268  -0.0900   0.3126   1.0000
   2.750   0.8917   0.00820   0.00281  -0.0898   0.3031   1.0000
   3.000   0.9189   0.00834   0.00292  -0.0897   0.2951   1.0000
   3.250   0.9456   0.00853   0.00305  -0.0895   0.2853   1.0000
   3.500   0.9722   0.00873   0.00318  -0.0893   0.2728   1.0000
   3.750   0.9987   0.00893   0.00332  -0.0891   0.2580   1.0000
   4.000   1.0241   0.00924   0.00349  -0.0888   0.2322   1.0000
   4.250   1.0470   0.00980   0.00379  -0.0881   0.1889   1.0000
   4.500   1.0715   0.01018   0.00406  -0.0876   0.1734   1.0000
   4.750   1.0967   0.01049   0.00432  -0.0873   0.1644   1.0000
   5.000   1.1224   0.01073   0.00454  -0.0870   0.1593   1.0000
   5.250   1.1475   0.01103   0.00480  -0.0866   0.1539   1.0000
   5.500   1.1728   0.01129   0.00505  -0.0863   0.1496   1.0000
   5.750   1.1987   0.01148   0.00526  -0.0861   0.1470   1.0000
   6.000   1.2241   0.01173   0.00550  -0.0858   0.1434   1.0000
   6.250   1.2484   0.01206   0.00579  -0.0853   0.1377   1.0000
   6.500   1.2736   0.01229   0.00603  -0.0850   0.1342   1.0000
   6.750   1.2989   0.01249   0.00625  -0.0847   0.1311   1.0000
   7.000   1.3235   0.01276   0.00650  -0.0844   0.1269   1.0000
   7.250   1.3470   0.01312   0.00683  -0.0838   0.1214   1.0000
   7.500   1.3721   0.01331   0.00705  -0.0836   0.1190   1.0000
   7.750   1.3962   0.01358   0.00731  -0.0831   0.1150   1.0000
   8.000   1.4192   0.01394   0.00764  -0.0826   0.1095   1.0000
   8.250   1.4430   0.01421   0.00793  -0.0821   0.1061   1.0000
   8.500   1.4659   0.01453   0.00824  -0.0815   0.1017   1.0000
   8.750   1.4876   0.01494   0.00862  -0.0808   0.0962   1.0000
   9.000   1.5102   0.01525   0.00895  -0.0802   0.0926   1.0000
   9.250   1.5311   0.01567   0.00934  -0.0793   0.0878   1.0000
   9.500   1.5518   0.01608   0.00976  -0.0785   0.0837   1.0000
   9.750   1.5722   0.01649   0.01018  -0.0775   0.0798   1.0000
  10.000   1.5904   0.01701   0.01067  -0.0763   0.0751   1.0000
  10.250   1.6095   0.01742   0.01111  -0.0752   0.0719   1.0000
  10.500   1.6248   0.01796   0.01163  -0.0734   0.0674   1.0000
  10.750   1.6392   0.01852   0.01220  -0.0715   0.0624   1.0000
  11.000   1.6509   0.01927   0.01290  -0.0694   0.0557   1.0000
  11.250   1.6606   0.02018   0.01376  -0.0671   0.0464   1.0000
  11.500   1.6549   0.02215   0.01554  -0.0630   0.0237   1.0000
  11.750   1.6567   0.02374   0.01713  -0.0602   0.0175   1.0000
  12.000   1.6642   0.02501   0.01845  -0.0582   0.0161   1.0000
  12.250   1.6719   0.02630   0.01981  -0.0564   0.0151   1.0000
  12.500   1.6812   0.02751   0.02109  -0.0549   0.0145   1.0000
  12.750   1.6888   0.02888   0.02254  -0.0534   0.0140   1.0000
  13.000   1.6947   0.03045   0.02419  -0.0519   0.0136   1.0000
  13.250   1.6986   0.03225   0.02606  -0.0504   0.0131   1.0000
  13.500   1.6996   0.03437   0.02829  -0.0490   0.0126   1.0000
  13.750   1.7030   0.03637   0.03037  -0.0478   0.0124   1.0000
  14.000   1.7073   0.03834   0.03244  -0.0470   0.0122   1.0000
  14.250   1.7097   0.04055   0.03474  -0.0462   0.0119   1.0000
  14.500   1.7109   0.04298   0.03726  -0.0455   0.0117   1.0000
  14.750   1.7106   0.04565   0.04003  -0.0450   0.0114   1.0000
  15.000   1.7084   0.04861   0.04310  -0.0447   0.0112   1.0000
  15.250   1.7047   0.05187   0.04645  -0.0446   0.0110   1.0000
  15.500   1.6987   0.05558   0.05027  -0.0447   0.0108   1.0000
  15.750   1.6903   0.05971   0.05452  -0.0451   0.0107   1.0000
  16.000   1.6787   0.06445   0.05938  -0.0458   0.0106   1.0000
  16.250   1.6645   0.06973   0.06479  -0.0469   0.0104   1.0000
  16.500   1.6470   0.07567   0.07087  -0.0483   0.0103   1.0000
  16.750   1.6283   0.08200   0.07735  -0.0501   0.0103   1.0000
  17.000   1.6057   0.08922   0.08472  -0.0525   0.0102   1.0000
  17.250   1.5831   0.09661   0.09226  -0.0550   0.0102   1.0000
  17.500   1.5594   0.10439   0.10019  -0.0579   0.0102   1.0000
  17.750   1.5358   0.11230   0.10824  -0.0611   0.0101   1.0000
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