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I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 961 (isa961-il)
Reynolds number: 200,000
Max Cl/Cd: 63.01 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa961-il-200000-n5.txt
Download as CSV file: xf-isa961-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3397   0.08958   0.08630  -0.0336   1.0000   0.0147
  -9.000  -0.3485   0.08745   0.08425  -0.0322   1.0000   0.0149
  -8.750  -0.3557   0.08463   0.08150  -0.0322   0.9977   0.0149
  -8.500  -0.3410   0.07881   0.07569  -0.0397   0.9897   0.0149
  -8.250  -0.3277   0.06906   0.06592  -0.0521   0.9800   0.0142
  -8.000  -0.3106   0.05695   0.05371  -0.0668   0.9698   0.0137
  -7.750  -0.2932   0.03291   0.02868  -0.0889   0.9583   0.0132
  -7.500  -0.2655   0.02693   0.02187  -0.0930   0.9536   0.0133
  -7.250  -0.2382   0.02392   0.01834  -0.0944   0.9482   0.0136
  -7.000  -0.2107   0.02125   0.01520  -0.0955   0.9427   0.0141
  -6.750  -0.1793   0.01956   0.01322  -0.0967   0.9389   0.0149
  -6.500  -0.1497   0.01847   0.01193  -0.0974   0.9336   0.0163
  -6.250  -0.1198   0.01746   0.01071  -0.0979   0.9281   0.0178
  -6.000  -0.0875   0.01650   0.00951  -0.0987   0.9238   0.0189
  -5.750  -0.0576   0.01571   0.00853  -0.0990   0.9180   0.0201
  -5.500  -0.0279   0.01489   0.00755  -0.0993   0.9120   0.0230
  -5.250   0.0039   0.01419   0.00676  -0.0999   0.9073   0.0288
  -5.000   0.0317   0.01374   0.00645  -0.0997   0.8990   0.0464
  -4.750   0.0628   0.01375   0.00628  -0.0999   0.8896   0.0657
  -4.500   0.0915   0.01363   0.00605  -0.0997   0.8770   0.0747
  -4.250   0.1186   0.01345   0.00574  -0.0992   0.8632   0.0827
  -4.000   0.1455   0.01327   0.00549  -0.0988   0.8502   0.0896
  -3.750   0.1725   0.01303   0.00516  -0.0984   0.8387   0.0949
  -3.500   0.1997   0.01277   0.00485  -0.0981   0.8280   0.0981
  -3.250   0.2272   0.01254   0.00454  -0.0977   0.8174   0.1007
  -3.000   0.2541   0.01235   0.00427  -0.0973   0.8049   0.1042
  -2.750   0.2810   0.01216   0.00403  -0.0968   0.7908   0.1079
  -2.500   0.3079   0.01200   0.00382  -0.0964   0.7750   0.1122
  -2.250   0.3348   0.01187   0.00360  -0.0959   0.7574   0.1177
  -2.000   0.3613   0.01177   0.00344  -0.0954   0.7370   0.1255
  -1.750   0.3879   0.01170   0.00329  -0.0949   0.7154   0.1376
  -1.500   0.4144   0.01166   0.00316  -0.0944   0.6950   0.1527
  -1.250   0.4408   0.01163   0.00307  -0.0940   0.6736   0.1700
  -1.000   0.4668   0.01163   0.00299  -0.0935   0.6498   0.1878
  -0.750   0.4927   0.01164   0.00294  -0.0930   0.6249   0.2066
  -0.500   0.5184   0.01167   0.00292  -0.0925   0.6007   0.2308
  -0.250   0.5438   0.01170   0.00293  -0.0920   0.5749   0.2653
   0.000   0.5686   0.01166   0.00297  -0.0915   0.5476   0.3341
   0.500   0.6272   0.01063   0.00311  -0.0920   0.4892   1.0000
   0.750   0.6517   0.01091   0.00319  -0.0913   0.4628   1.0000
   1.000   0.6756   0.01124   0.00330  -0.0906   0.4337   1.0000
   1.250   0.6992   0.01161   0.00345  -0.0899   0.4023   1.0000
   1.500   0.7226   0.01200   0.00361  -0.0891   0.3693   1.0000
   1.750   0.7462   0.01239   0.00378  -0.0885   0.3371   1.0000
   2.000   0.7703   0.01273   0.00397  -0.0879   0.3121   1.0000
   2.250   0.7950   0.01303   0.00416  -0.0874   0.2947   1.0000
   2.500   0.8196   0.01334   0.00436  -0.0869   0.2786   1.0000
   2.750   0.8438   0.01368   0.00459  -0.0864   0.2618   1.0000
   3.000   0.8683   0.01399   0.00483  -0.0859   0.2482   1.0000
   3.250   0.8927   0.01431   0.00507  -0.0854   0.2361   1.0000
   3.500   0.9169   0.01464   0.00535  -0.0849   0.2239   1.0000
   3.750   0.9409   0.01499   0.00563  -0.0844   0.2112   1.0000
   4.000   0.9650   0.01532   0.00592  -0.0839   0.1973   1.0000
   4.250   0.9886   0.01569   0.00625  -0.0834   0.1761   1.0000
   4.500   1.0085   0.01643   0.00670  -0.0823   0.1360   1.0000
   4.750   1.0312   0.01687   0.00710  -0.0817   0.1287   1.0000
   5.000   1.0546   0.01724   0.00748  -0.0811   0.1257   1.0000
   5.250   1.0779   0.01760   0.00789  -0.0805   0.1230   1.0000
   5.500   1.1008   0.01799   0.00832  -0.0798   0.1203   1.0000
   5.750   1.1229   0.01844   0.00880  -0.0791   0.1167   1.0000
   6.000   1.1453   0.01885   0.00926  -0.0784   0.1144   1.0000
   6.250   1.1681   0.01920   0.00972  -0.0777   0.1130   1.0000
   6.500   1.1905   0.01957   0.01019  -0.0770   0.1108   1.0000
   6.750   1.2113   0.02007   0.01074  -0.0761   0.1053   1.0000
   7.000   1.2313   0.02062   0.01131  -0.0751   0.0967   1.0000
   7.250   1.2514   0.02115   0.01183  -0.0742   0.0683   1.0000
   7.500   1.2664   0.02207   0.01261  -0.0726   0.0598   1.0000
   7.750   1.2816   0.02291   0.01349  -0.0709   0.0555   1.0000
   8.000   1.2952   0.02378   0.01443  -0.0690   0.0518   1.0000
   8.250   1.3106   0.02439   0.01516  -0.0673   0.0481   1.0000
   8.500   1.3239   0.02517   0.01603  -0.0654   0.0436   1.0000
   8.750   1.3395   0.02580   0.01676  -0.0638   0.0385   1.0000
   9.000   1.3482   0.02695   0.01779  -0.0615   0.0180   1.0000
   9.250   1.3549   0.02830   0.01920  -0.0591   0.0153   1.0000
   9.500   1.3622   0.02964   0.02070  -0.0568   0.0138   1.0000
   9.750   1.3692   0.03104   0.02226  -0.0547   0.0128   1.0000
  10.000   1.3766   0.03245   0.02383  -0.0528   0.0123   1.0000
  10.250   1.3827   0.03401   0.02555  -0.0510   0.0117   1.0000
  10.500   1.3871   0.03577   0.02748  -0.0493   0.0111   1.0000
  10.750   1.3895   0.03777   0.02965  -0.0476   0.0105   1.0000
  11.000   1.3898   0.04006   0.03210  -0.0461   0.0100   1.0000
  11.250   1.3878   0.04269   0.03490  -0.0449   0.0096   1.0000
  11.500   1.3835   0.04571   0.03809  -0.0439   0.0094   1.0000
  11.750   1.3772   0.04911   0.04166  -0.0432   0.0092   1.0000
  12.000   1.3681   0.05305   0.04577  -0.0429   0.0090   1.0000
  12.250   1.3573   0.05739   0.05029  -0.0431   0.0088   1.0000
  12.500   1.3453   0.06213   0.05519  -0.0436   0.0087   1.0000
  12.750   1.3379   0.06648   0.05968  -0.0444   0.0087   1.0000
  13.000   1.3303   0.07101   0.06435  -0.0453   0.0086   1.0000
  13.250   1.3222   0.07577   0.06926  -0.0465   0.0085   1.0000
  13.500   1.3139   0.08071   0.07437  -0.0479   0.0084   1.0000
  13.750   1.3054   0.08574   0.07954  -0.0493   0.0083   1.0000
  14.000   1.2971   0.09082   0.08476  -0.0509   0.0083   1.0000
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