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S2091-101-83 (s2091-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S2091-101-83 (s2091-il)
Reynolds number: 500,000
Max Cl/Cd: 107.44 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2091-il-500000.txt
Download as CSV file: xf-s2091-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2091-101-83                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3234   0.09332   0.09113  -0.0304   1.0000   0.0216
  -8.750  -0.3202   0.08985   0.08770  -0.0322   1.0000   0.0228
  -8.000  -0.3261   0.07395   0.07195  -0.0455   0.9839   0.0246
  -7.750  -0.3007   0.07227   0.07025  -0.0479   0.9731   0.0253
  -7.500  -0.2827   0.06666   0.06461  -0.0566   0.9523   0.0255
  -7.250  -0.2692   0.06401   0.06190  -0.0597   0.9329   0.0267
  -7.000  -0.3175   0.03360   0.03065  -0.0827   0.8993   0.0187
  -6.750  -0.3184   0.02149   0.01716  -0.0851   0.8869   0.0177
  -6.500  -0.2964   0.01915   0.01436  -0.0847   0.8788   0.0183
  -6.250  -0.2722   0.01753   0.01237  -0.0843   0.8706   0.0190
  -6.000  -0.2464   0.01660   0.01113  -0.0839   0.8629   0.0196
  -5.750  -0.2221   0.01493   0.00930  -0.0836   0.8550   0.0208
  -5.500  -0.1954   0.01451   0.00880  -0.0834   0.8474   0.0222
  -5.250  -0.1685   0.01397   0.00810  -0.0830   0.8395   0.0237
  -5.000  -0.1422   0.01292   0.00689  -0.0827   0.8321   0.0251
  -4.750  -0.1153   0.01240   0.00633  -0.0825   0.8242   0.0267
  -4.500  -0.0879   0.01200   0.00583  -0.0822   0.8166   0.0287
  -4.250  -0.0608   0.01140   0.00514  -0.0820   0.8087   0.0311
  -4.000  -0.0333   0.01107   0.00478  -0.0818   0.8011   0.0336
  -3.750  -0.0055   0.01078   0.00441  -0.0816   0.7930   0.0361
  -3.500   0.0219   0.01032   0.00392  -0.0814   0.7854   0.0401
  -3.250   0.0499   0.01010   0.00365  -0.0812   0.7772   0.0441
  -3.000   0.0777   0.00975   0.00328  -0.0811   0.7692   0.0507
  -2.750   0.1056   0.00947   0.00298  -0.0810   0.7610   0.0603
  -2.500   0.1337   0.00924   0.00275  -0.0809   0.7526   0.0726
  -2.250   0.1617   0.00906   0.00255  -0.0808   0.7443   0.0860
  -2.000   0.1899   0.00888   0.00239  -0.0807   0.7354   0.1013
  -1.750   0.2178   0.00873   0.00223  -0.0806   0.7272   0.1225
  -1.500   0.2459   0.00848   0.00212  -0.0806   0.7177   0.1615
  -1.250   0.2736   0.00818   0.00202  -0.0806   0.7091   0.2345
  -1.000   0.3010   0.00783   0.00197  -0.0807   0.6997   0.3390
  -0.750   0.3284   0.00752   0.00195  -0.0806   0.6903   0.4474
  -0.500   0.3552   0.00725   0.00194  -0.0804   0.6813   0.5555
  -0.250   0.3817   0.00695   0.00195  -0.0800   0.6710   0.6631
   0.000   0.4048   0.00658   0.00198  -0.0786   0.6615   0.8027
   0.250   0.4399   0.00626   0.00190  -0.0795   0.6512   1.0000
   0.500   0.4680   0.00633   0.00188  -0.0794   0.6403   1.0000
   0.750   0.4959   0.00641   0.00187  -0.0793   0.6298   1.0000
   1.000   0.5237   0.00651   0.00186  -0.0792   0.6192   1.0000
   1.250   0.5517   0.00659   0.00188  -0.0791   0.6078   1.0000
   1.500   0.5796   0.00669   0.00190  -0.0790   0.5964   1.0000
   1.750   0.6074   0.00680   0.00193  -0.0789   0.5850   1.0000
   2.000   0.6350   0.00693   0.00197  -0.0788   0.5733   1.0000
   2.250   0.6628   0.00704   0.00203  -0.0787   0.5608   1.0000
   2.500   0.6905   0.00716   0.00209  -0.0786   0.5483   1.0000
   2.750   0.7180   0.00729   0.00216  -0.0784   0.5356   1.0000
   3.000   0.7455   0.00744   0.00225  -0.0783   0.5227   1.0000
   3.250   0.7728   0.00760   0.00234  -0.0782   0.5096   1.0000
   3.500   0.8000   0.00777   0.00245  -0.0780   0.4963   1.0000
   3.750   0.8271   0.00795   0.00256  -0.0779   0.4825   1.0000
   4.000   0.8542   0.00812   0.00270  -0.0777   0.4684   1.0000
   4.250   0.8811   0.00831   0.00283  -0.0775   0.4541   1.0000
   4.500   0.9079   0.00851   0.00299  -0.0774   0.4396   1.0000
   4.750   0.9346   0.00872   0.00316  -0.0772   0.4249   1.0000
   5.000   0.9610   0.00895   0.00334  -0.0770   0.4098   1.0000
   5.250   0.9874   0.00919   0.00353  -0.0767   0.3947   1.0000
   5.500   1.0135   0.00945   0.00374  -0.0765   0.3794   1.0000
   5.750   1.0393   0.00972   0.00396  -0.0762   0.3636   1.0000
   6.000   1.0650   0.01001   0.00420  -0.0759   0.3481   1.0000
   6.250   1.0905   0.01031   0.00445  -0.0756   0.3326   1.0000
   6.500   1.1156   0.01063   0.00473  -0.0753   0.3168   1.0000
   7.000   1.1654   0.01131   0.00531  -0.0745   0.2856   1.0000
   7.250   1.1899   0.01166   0.00564  -0.0741   0.2703   1.0000
   7.500   1.2141   0.01204   0.00597  -0.0737   0.2554   1.0000
   7.750   1.2380   0.01243   0.00633  -0.0732   0.2410   1.0000
   8.000   1.2615   0.01284   0.00671  -0.0727   0.2268   1.0000
   8.250   1.2846   0.01327   0.00710  -0.0721   0.2124   1.0000
   8.500   1.3073   0.01373   0.00752  -0.0715   0.1981   1.0000
   8.750   1.3295   0.01421   0.00797  -0.0708   0.1836   1.0000
   9.000   1.3511   0.01471   0.00844  -0.0700   0.1690   1.0000
   9.250   1.3719   0.01526   0.00895  -0.0692   0.1540   1.0000
   9.500   1.3918   0.01585   0.00950  -0.0682   0.1390   1.0000
   9.750   1.4106   0.01650   0.01010  -0.0671   0.1237   1.0000
  10.000   1.4280   0.01721   0.01076  -0.0658   0.1092   1.0000
  10.250   1.4440   0.01798   0.01147  -0.0644   0.0956   1.0000
  10.500   1.4586   0.01878   0.01223  -0.0628   0.0838   1.0000
  10.750   1.4704   0.01959   0.01301  -0.0607   0.0742   1.0000
  11.000   1.4789   0.02048   0.01389  -0.0581   0.0663   1.0000
  11.250   1.4873   0.02143   0.01485  -0.0558   0.0597   1.0000
  11.500   1.4960   0.02241   0.01587  -0.0537   0.0544   1.0000
  11.750   1.5029   0.02358   0.01705  -0.0516   0.0497   1.0000
  12.000   1.5096   0.02483   0.01835  -0.0496   0.0458   1.0000
  12.250   1.5173   0.02606   0.01964  -0.0480   0.0425   1.0000
  12.500   1.5186   0.02787   0.02147  -0.0460   0.0392   1.0000
  12.750   1.5262   0.02927   0.02297  -0.0447   0.0370   1.0000
  13.000   1.5319   0.03089   0.02467  -0.0435   0.0346   1.0000
  13.250   1.5318   0.03311   0.02692  -0.0422   0.0322   1.0000
  13.500   1.5317   0.03545   0.02937  -0.0411   0.0307   1.0000
  13.750   1.5377   0.03731   0.03133  -0.0405   0.0291   1.0000
  14.000   1.5397   0.03962   0.03372  -0.0399   0.0276   1.0000
  14.250   1.5370   0.04255   0.03671  -0.0395   0.0263   1.0000
  14.500   1.5269   0.04644   0.04070  -0.0393   0.0252   1.0000
  14.750   1.5289   0.04909   0.04348  -0.0393   0.0243   1.0000
  15.000   1.5300   0.05194   0.04643  -0.0395   0.0232   1.0000
  15.250   1.5279   0.05530   0.04991  -0.0399   0.0224   1.0000
  15.500   1.5243   0.05899   0.05369  -0.0406   0.0216   1.0000
  15.750   1.5159   0.06350   0.05829  -0.0417   0.0208   1.0000
  16.000   1.5036   0.06870   0.06358  -0.0431   0.0202   1.0000
  16.250   1.4952   0.07354   0.06855  -0.0446   0.0197   1.0000
  16.500   1.4931   0.07758   0.07273  -0.0459   0.0191   1.0000
  16.750   1.4888   0.08205   0.07731  -0.0475   0.0185   1.0000
  17.000   1.4815   0.08710   0.08248  -0.0494   0.0181   1.0000
  17.250   1.4752   0.09209   0.08758  -0.0515   0.0176   1.0000
  17.500   1.4674   0.09743   0.09302  -0.0537   0.0171   1.0000
  17.750   1.4583   0.10306   0.09874  -0.0562   0.0167   1.0000
  18.000   1.4482   0.10893   0.10470  -0.0589   0.0163   1.0000
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