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I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 962 (isa962-il)
Reynolds number: 500,000
Max Cl/Cd: 98.66 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa962-il-500000.txt
Download as CSV file: xf-isa962-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3071   0.09316   0.09084  -0.0310   1.0000   0.0295
  -9.250  -0.3069   0.09091   0.08864  -0.0308   1.0000   0.0299
  -9.000  -0.3121   0.08910   0.08688  -0.0297   0.9992   0.0303
  -8.750  -0.2944   0.08482   0.08260  -0.0357   0.9941   0.0316
  -8.500  -0.2669   0.07458   0.07229  -0.0596   0.9808   0.0329
  -8.250  -0.2531   0.07089   0.06861  -0.0603   0.9750   0.0332
  -8.000  -0.2310   0.06800   0.06570  -0.0630   0.9697   0.0335
  -7.750  -0.2095   0.06508   0.06276  -0.0662   0.9609   0.0339
  -7.500  -0.1870   0.06189   0.05954  -0.0701   0.9518   0.0345
  -7.250  -0.1643   0.05839   0.05598  -0.0745   0.9418   0.0353
  -7.000  -0.1298   0.04689   0.04411  -0.0906   0.9291   0.0387
  -6.750  -0.1130   0.04501   0.04219  -0.0904   0.9189   0.0391
  -6.500  -0.0933   0.04327   0.04038  -0.0907   0.9102   0.0395
  -6.250  -0.0724   0.04135   0.03839  -0.0913   0.9009   0.0401
  -6.000  -0.0494   0.03902   0.03595  -0.0925   0.8929   0.0411
  -5.750  -0.0205   0.03093   0.02722  -0.0973   0.8843   0.0457
  -5.500   0.0022   0.02960   0.02586  -0.0973   0.8765   0.0462
  -5.250   0.0259   0.02838   0.02458  -0.0972   0.8675   0.0470
  -5.000   0.0505   0.02696   0.02304  -0.0972   0.8592   0.0483
  -4.750   0.0770   0.02357   0.01912  -0.0977   0.8505   0.0539
  -4.500   0.1021   0.02254   0.01808  -0.0976   0.8418   0.0549
  -4.250   0.1280   0.02156   0.01701  -0.0974   0.8325   0.0565
  -4.000   0.1562   0.01598   0.01035  -0.0968   0.8240   0.0463
  -3.750   0.1836   0.01437   0.00851  -0.0963   0.8146   0.0419
  -3.500   0.2115   0.01302   0.00683  -0.0958   0.8040   0.0402
  -3.250   0.2390   0.01244   0.00614  -0.0955   0.7933   0.0406
  -3.000   0.2665   0.01193   0.00553  -0.0951   0.7816   0.0411
  -2.750   0.2941   0.01140   0.00490  -0.0947   0.7688   0.0412
  -2.500   0.3215   0.01098   0.00439  -0.0943   0.7550   0.0416
  -2.250   0.3489   0.01063   0.00396  -0.0940   0.7413   0.0421
  -2.000   0.3764   0.01036   0.00361  -0.0936   0.7284   0.0428
  -1.750   0.4039   0.01014   0.00332  -0.0933   0.7160   0.0435
  -1.500   0.4315   0.00995   0.00309  -0.0930   0.7033   0.0443
  -1.250   0.4592   0.00978   0.00287  -0.0928   0.6914   0.0452
  -1.000   0.4865   0.00954   0.00260  -0.0925   0.6799   0.0477
  -0.750   0.5144   0.00943   0.00248  -0.0923   0.6684   0.0500
  -0.500   0.5422   0.00936   0.00236  -0.0921   0.6569   0.0524
  -0.250   0.5698   0.00926   0.00225  -0.0919   0.6450   0.0582
   0.000   0.5971   0.00912   0.00223  -0.0917   0.6311   0.1093
   0.250   0.6238   0.00879   0.00229  -0.0916   0.6163   0.2574
   0.500   0.6473   0.00788   0.00241  -0.0911   0.6020   0.6513
   0.750   0.6829   0.00727   0.00243  -0.0924   0.5861   1.0000
   1.000   0.7098   0.00740   0.00246  -0.0921   0.5695   1.0000
   1.250   0.7364   0.00756   0.00251  -0.0917   0.5511   1.0000
   1.500   0.7628   0.00774   0.00256  -0.0914   0.5289   1.0000
   1.750   0.7883   0.00799   0.00264  -0.0908   0.4975   1.0000
   2.000   0.8134   0.00829   0.00275  -0.0903   0.4606   1.0000
   2.250   0.8380   0.00864   0.00290  -0.0897   0.4234   1.0000
   2.500   0.8626   0.00902   0.00308  -0.0891   0.3910   1.0000
   2.750   0.8875   0.00937   0.00328  -0.0887   0.3688   1.0000
   3.000   0.9129   0.00968   0.00348  -0.0882   0.3525   1.0000
   3.250   0.9385   0.00996   0.00368  -0.0879   0.3390   1.0000
   3.500   0.9643   0.01020   0.00387  -0.0876   0.3270   1.0000
   3.750   0.9900   0.01046   0.00407  -0.0872   0.3161   1.0000
   4.000   1.0152   0.01076   0.00430  -0.0868   0.3038   1.0000
   4.250   1.0410   0.01099   0.00449  -0.0865   0.2903   1.0000
   4.500   1.0664   0.01126   0.00470  -0.0862   0.2742   1.0000
   4.750   1.0912   0.01158   0.00493  -0.0857   0.2519   1.0000
   5.000   1.1145   0.01203   0.00520  -0.0851   0.2182   1.0000
   5.250   1.1367   0.01257   0.00555  -0.0843   0.1933   1.0000
   5.750   1.1829   0.01346   0.00632  -0.0830   0.1733   1.0000
   6.000   1.2050   0.01397   0.00676  -0.0822   0.1662   1.0000
   6.250   1.2289   0.01429   0.00712  -0.0817   0.1619   1.0000
   6.500   1.2520   0.01468   0.00752  -0.0810   0.1573   1.0000
   6.750   1.2732   0.01521   0.00801  -0.0801   0.1524   1.0000
   7.000   1.2959   0.01559   0.00842  -0.0795   0.1482   1.0000
   7.250   1.3194   0.01589   0.00877  -0.0789   0.1436   1.0000
   7.500   1.3405   0.01637   0.00922  -0.0780   0.1386   1.0000
   7.750   1.3614   0.01684   0.00970  -0.0771   0.1343   1.0000
   8.000   1.3848   0.01710   0.01001  -0.0766   0.1303   1.0000
   8.250   1.4060   0.01750   0.01042  -0.0758   0.1259   1.0000
   8.500   1.4241   0.01811   0.01101  -0.0745   0.1214   1.0000
   8.750   1.4465   0.01838   0.01136  -0.0738   0.1184   1.0000
   9.000   1.4669   0.01875   0.01177  -0.0729   0.1145   1.0000
   9.250   1.4843   0.01927   0.01227  -0.0715   0.1104   1.0000
   9.500   1.5012   0.01974   0.01278  -0.0699   0.1067   1.0000
   9.750   1.5193   0.02014   0.01323  -0.0687   0.1030   1.0000
  10.000   1.5351   0.02068   0.01378  -0.0671   0.0994   1.0000
  10.250   1.5486   0.02139   0.01450  -0.0653   0.0959   1.0000
  10.500   1.5660   0.02188   0.01506  -0.0641   0.0930   1.0000
  10.750   1.5814   0.02250   0.01572  -0.0627   0.0895   1.0000
  11.000   1.5940   0.02333   0.01655  -0.0611   0.0859   1.0000
  11.250   1.6093   0.02400   0.01730  -0.0599   0.0826   1.0000
  11.500   1.6235   0.02476   0.01811  -0.0587   0.0790   1.0000
  11.750   1.6345   0.02579   0.01913  -0.0572   0.0751   1.0000
  12.000   1.6485   0.02661   0.02004  -0.0561   0.0716   1.0000
  12.250   1.6595   0.02769   0.02113  -0.0548   0.0665   1.0000
  12.500   1.6700   0.02884   0.02230  -0.0535   0.0602   1.0000
  12.750   1.6765   0.03035   0.02379  -0.0520   0.0518   1.0000
  13.000   1.6756   0.03254   0.02590  -0.0502   0.0380   1.0000
  13.250   1.6657   0.03565   0.02891  -0.0481   0.0249   1.0000
  13.500   1.6614   0.03842   0.03172  -0.0466   0.0216   1.0000
  13.750   1.6602   0.04099   0.03439  -0.0456   0.0203   1.0000
  14.000   1.6577   0.04381   0.03732  -0.0447   0.0194   1.0000
  14.250   1.6530   0.04699   0.04061  -0.0441   0.0186   1.0000
  14.500   1.6481   0.05030   0.04404  -0.0437   0.0181   1.0000
  14.750   1.6442   0.05363   0.04750  -0.0436   0.0177   1.0000
  15.000   1.6380   0.05738   0.05139  -0.0438   0.0174   1.0000
  15.250   1.6301   0.06150   0.05565  -0.0442   0.0171   1.0000
  15.500   1.6202   0.06605   0.06034  -0.0449   0.0168   1.0000
  15.750   1.6082   0.07108   0.06550  -0.0459   0.0166   1.0000
  16.000   1.5940   0.07657   0.07114  -0.0473   0.0164   1.0000
  16.250   1.5781   0.08252   0.07724  -0.0490   0.0163   1.0000
  16.500   1.5601   0.08902   0.08389  -0.0512   0.0162   1.0000
  16.750   1.5413   0.09581   0.09083  -0.0535   0.0161   1.0000
  17.000   1.5208   0.10308   0.09825  -0.0563   0.0160   1.0000
  17.250   1.5005   0.11045   0.10577  -0.0592   0.0159   1.0000
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