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Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Curtis C-72 (curtisc72-il)
Reynolds number: 500,000
Max Cl/Cd: 103.37 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-curtisc72-il-500000.txt
Download as CSV file: xf-curtisc72-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Curtis C-72                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3746   0.08709   0.08478  -0.0431   1.0000   0.0378
 -11.000  -0.3842   0.08395   0.08169  -0.0430   1.0000   0.0388
 -10.500  -0.4699   0.03393   0.03040  -0.0975   0.9765   0.0356
 -10.250  -0.4426   0.02964   0.02561  -0.1005   0.9733   0.0342
 -10.000  -0.4124   0.02641   0.02194  -0.1034   0.9712   0.0343
  -9.750  -0.3900   0.02339   0.01850  -0.1042   0.9650   0.0349
  -9.500  -0.3622   0.02078   0.01565  -0.1054   0.9610   0.0355
  -9.250  -0.3308   0.01920   0.01390  -0.1066   0.9581   0.0359
  -9.000  -0.3039   0.01806   0.01264  -0.1066   0.9523   0.0363
  -8.750  -0.2753   0.01705   0.01151  -0.1069   0.9468   0.0369
  -8.500  -0.2450   0.01622   0.01058  -0.1074   0.9426   0.0376
  -8.250  -0.2193   0.01552   0.00979  -0.1068   0.9349   0.0384
  -8.000  -0.1913   0.01473   0.00890  -0.1067   0.9290   0.0389
  -7.750  -0.1647   0.01404   0.00811  -0.1063   0.9219   0.0394
  -7.500  -0.1379   0.01342   0.00740  -0.1059   0.9147   0.0399
  -7.250  -0.1108   0.01289   0.00679  -0.1055   0.9077   0.0404
  -7.000  -0.0843   0.01244   0.00627  -0.1050   0.8997   0.0409
  -6.750  -0.0579   0.01180   0.00555  -0.1046   0.8926   0.0418
  -6.500  -0.0321   0.01124   0.00496  -0.1040   0.8841   0.0431
  -6.250  -0.0049   0.01088   0.00456  -0.1037   0.8769   0.0441
  -6.000   0.0218   0.01056   0.00421  -0.1033   0.8681   0.0453
  -5.750   0.0490   0.01029   0.00388  -0.1029   0.8597   0.0466
  -5.500   0.0760   0.01004   0.00357  -0.1025   0.8497   0.0481
  -5.250   0.1029   0.00976   0.00323  -0.1020   0.8391   0.0503
  -5.000   0.1302   0.00952   0.00297  -0.1017   0.8289   0.0542
  -4.750   0.1573   0.00931   0.00274  -0.1013   0.8175   0.0613
  -4.500   0.1844   0.00902   0.00253  -0.1010   0.8067   0.0858
  -4.250   0.2116   0.00872   0.00234  -0.1008   0.7974   0.1278
  -4.000   0.2386   0.00842   0.00222  -0.1006   0.7875   0.1877
  -3.750   0.2654   0.00810   0.00212  -0.1005   0.7779   0.2626
  -3.500   0.2921   0.00780   0.00206  -0.1002   0.7681   0.3529
  -3.250   0.3190   0.00762   0.00207  -0.1000   0.7577   0.4287
  -3.000   0.3464   0.00755   0.00207  -0.0998   0.7483   0.4726
  -2.750   0.3738   0.00752   0.00206  -0.0995   0.7380   0.5036
  -2.500   0.4012   0.00749   0.00206  -0.0993   0.7275   0.5312
  -2.250   0.4285   0.00748   0.00206  -0.0990   0.7172   0.5582
  -2.000   0.4556   0.00744   0.00207  -0.0987   0.7066   0.5874
  -1.750   0.4826   0.00739   0.00209  -0.0985   0.6963   0.6206
  -1.500   0.5094   0.00736   0.00211  -0.0981   0.6859   0.6547
  -1.250   0.5354   0.00725   0.00213  -0.0976   0.6744   0.7045
  -1.000   0.5577   0.00693   0.00219  -0.0962   0.6630   0.8161
  -0.750   0.6005   0.00675   0.00219  -0.0990   0.6508   1.0000
  -0.500   0.6271   0.00687   0.00222  -0.0987   0.6390   1.0000
  -0.250   0.6538   0.00697   0.00225  -0.0985   0.6260   1.0000
   0.000   0.6804   0.00709   0.00230  -0.0982   0.6122   1.0000
   0.250   0.7068   0.00722   0.00235  -0.0979   0.5977   1.0000
   0.500   0.7332   0.00735   0.00242  -0.0976   0.5829   1.0000
   0.750   0.7593   0.00751   0.00250  -0.0972   0.5668   1.0000
   1.000   0.7851   0.00768   0.00258  -0.0968   0.5490   1.0000
   1.250   0.8106   0.00788   0.00269  -0.0964   0.5300   1.0000
   1.500   0.8361   0.00809   0.00281  -0.0960   0.5094   1.0000
   1.750   0.8611   0.00833   0.00294  -0.0955   0.4862   1.0000
   2.000   0.8856   0.00861   0.00311  -0.0950   0.4617   1.0000
   2.250   0.9097   0.00892   0.00329  -0.0944   0.4355   1.0000
   2.500   0.9340   0.00924   0.00348  -0.0939   0.4113   1.0000
   2.750   0.9585   0.00955   0.00369  -0.0935   0.3917   1.0000
   3.000   0.9835   0.00982   0.00390  -0.0931   0.3776   1.0000
   3.250   1.0086   0.01009   0.00413  -0.0927   0.3660   1.0000
   3.750   1.0587   0.01063   0.00460  -0.0921   0.3449   1.0000
   4.000   1.0836   0.01090   0.00484  -0.0918   0.3355   1.0000
   4.250   1.1085   0.01117   0.00510  -0.0914   0.3267   1.0000
   4.500   1.1336   0.01142   0.00536  -0.0912   0.3188   1.0000
   4.750   1.1581   0.01171   0.00563  -0.0908   0.3104   1.0000
   5.000   1.1831   0.01195   0.00589  -0.0905   0.3024   1.0000
   5.250   1.2068   0.01228   0.00619  -0.0900   0.2929   1.0000
   5.500   1.2314   0.01252   0.00645  -0.0897   0.2807   1.0000
   5.750   1.2548   0.01284   0.00673  -0.0893   0.2649   1.0000
   6.000   1.2772   0.01322   0.00705  -0.0887   0.2470   1.0000
   6.250   1.2995   0.01361   0.00738  -0.0880   0.2274   1.0000
   6.500   1.3201   0.01411   0.00778  -0.0872   0.2045   1.0000
   6.750   1.3391   0.01473   0.00827  -0.0861   0.1799   1.0000
   7.000   1.3565   0.01543   0.00886  -0.0848   0.1578   1.0000
   7.250   1.3741   0.01610   0.00945  -0.0836   0.1398   1.0000
   7.500   1.3911   0.01678   0.01006  -0.0822   0.1250   1.0000
   7.750   1.4067   0.01743   0.01067  -0.0806   0.1132   1.0000
   8.000   1.4216   0.01810   0.01131  -0.0789   0.1029   1.0000
   8.250   1.4358   0.01883   0.01200  -0.0772   0.0934   1.0000
   8.500   1.4507   0.01950   0.01269  -0.0756   0.0845   1.0000
   8.750   1.4638   0.02031   0.01347  -0.0739   0.0737   1.0000
   9.000   1.4731   0.02137   0.01444  -0.0717   0.0577   1.0000
   9.250   1.4772   0.02281   0.01575  -0.0691   0.0405   1.0000
   9.500   1.4824   0.02423   0.01714  -0.0668   0.0331   1.0000
   9.750   1.4870   0.02574   0.01867  -0.0645   0.0293   1.0000
  10.000   1.4953   0.02703   0.02004  -0.0628   0.0271   1.0000
  10.250   1.4995   0.02868   0.02173  -0.0610   0.0254   1.0000
  10.500   1.5028   0.03048   0.02362  -0.0592   0.0240   1.0000
  10.750   1.5091   0.03208   0.02533  -0.0579   0.0230   1.0000
  11.000   1.5138   0.03390   0.02723  -0.0566   0.0220   1.0000
  11.250   1.5155   0.03605   0.02945  -0.0554   0.0212   1.0000
  11.500   1.5113   0.03888   0.03236  -0.0541   0.0204   1.0000
  11.750   1.5098   0.04155   0.03514  -0.0532   0.0199   1.0000
  12.000   1.5117   0.04397   0.03768  -0.0526   0.0194   1.0000
  12.250   1.5114   0.04671   0.04053  -0.0521   0.0189   1.0000
  12.500   1.5095   0.04971   0.04363  -0.0518   0.0184   1.0000
  12.750   1.5064   0.05297   0.04700  -0.0517   0.0180   1.0000
  13.000   1.5021   0.05650   0.05063  -0.0518   0.0177   1.0000
  13.250   1.4962   0.06034   0.05456  -0.0520   0.0174   1.0000
  13.500   1.4880   0.06459   0.05890  -0.0525   0.0171   1.0000
  13.750   1.4776   0.06923   0.06364  -0.0531   0.0168   1.0000
  14.000   1.4648   0.07423   0.06874  -0.0539   0.0166   1.0000
  14.250   1.4568   0.07871   0.07332  -0.0547   0.0164   1.0000
  14.500   1.4523   0.08285   0.07758  -0.0557   0.0162   1.0000
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