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N-24 (n24-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: N-24 (n24-il)
Reynolds number: 100,000
Max Cl/Cd: 41.49 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n24-il-100000.txt
Download as CSV file: xf-n24-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-24                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0979   0.09928   0.09456  -0.0726   0.9573   0.1497
 -10.750  -0.0871   0.09638   0.09166  -0.0757   0.9481   0.1550
 -10.500  -0.1401   0.09383   0.08919  -0.0866   0.9299   0.1599
 -10.250  -0.0873   0.08933   0.08465  -0.0834   0.9287   0.1619
 -10.000  -0.0717   0.08701   0.08233  -0.0821   0.9179   0.1643
  -9.750  -0.0648   0.08469   0.08002  -0.0821   0.9072   0.1676
  -9.500  -0.2074   0.05918   0.05375  -0.1050   0.8844   0.1047
  -9.250  -0.1943   0.05636   0.05088  -0.1046   0.8761   0.1036
  -9.000  -0.1889   0.05221   0.04650  -0.1047   0.8670   0.1019
  -8.750  -0.1867   0.04739   0.04120  -0.1046   0.8587   0.1011
  -8.500  -0.1788   0.04355   0.03685  -0.1038   0.8496   0.1020
  -8.250  -0.1598   0.03976   0.03238  -0.1035   0.8451   0.1037
  -8.000  -0.1499   0.03765   0.02973  -0.1015   0.8332   0.1053
  -7.750  -0.1207   0.03619   0.02831  -0.1014   0.8284   0.1085
  -7.500  -0.1020   0.03532   0.02727  -0.1002   0.8190   0.1123
  -7.250  -0.0777   0.03383   0.02544  -0.0995   0.8124   0.1189
  -7.000  -0.0479   0.03288   0.02425  -0.0989   0.8084   0.1292
  -6.750  -0.0298   0.03270   0.02422  -0.0978   0.7976   0.1372
  -6.500  -0.0014   0.03179   0.02316  -0.0973   0.7923   0.1490
  -6.250   0.0287   0.03108   0.02221  -0.0968   0.7888   0.1609
  -6.000   0.0462   0.03136   0.02261  -0.0959   0.7775   0.1685
  -5.750   0.0759   0.03074   0.02185  -0.0955   0.7729   0.1795
  -5.500   0.1065   0.03033   0.02137  -0.0950   0.7695   0.1923
  -5.250   0.1235   0.03060   0.02172  -0.0943   0.7579   0.1998
  -5.000   0.1549   0.02987   0.02086  -0.0939   0.7535   0.2093
  -4.750   0.1800   0.02939   0.02032  -0.0932   0.7455   0.2163
  -4.500   0.2075   0.02877   0.01970  -0.0925   0.7376   0.2243
  -4.250   0.2403   0.02764   0.01845  -0.0919   0.7333   0.2348
  -4.000   0.2622   0.02765   0.01854  -0.0912   0.7233   0.2470
  -3.750   0.2913   0.02695   0.01789  -0.0907   0.7176   0.2668
  -3.500   0.3224   0.02601   0.01703  -0.0901   0.7139   0.2956
  -3.250   0.3423   0.02627   0.01749  -0.0895   0.7036   0.3254
  -3.000   0.3713   0.02557   0.01695  -0.0889   0.6983   0.3694
  -2.750   0.4023   0.02459   0.01623  -0.0883   0.6947   0.4358
  -2.500   0.4210   0.02469   0.01690  -0.0874   0.6842   0.5390
  -2.250   0.5077   0.02286   0.01607  -0.0964   0.6792   1.0002
  -2.000   0.5358   0.02269   0.01562  -0.0958   0.6739   1.0002
  -1.750   0.5568   0.02321   0.01601  -0.0950   0.6639   1.0002
  -1.500   0.5867   0.02286   0.01543  -0.0945   0.6588   1.0002
  -1.250   0.6083   0.02337   0.01584  -0.0938   0.6495   1.0002
  -1.000   0.6360   0.02324   0.01554  -0.0933   0.6426   1.0002
  -0.750   0.6658   0.02300   0.01510  -0.0929   0.6369   1.0002
  -0.500   0.6871   0.02347   0.01552  -0.0921   0.6263   1.0002
  -0.250   0.7188   0.02307   0.01491  -0.0919   0.6208   1.0002
   0.000   0.7391   0.02368   0.01550  -0.0911   0.6099   1.0002
   0.250   0.7700   0.02339   0.01503  -0.0909   0.6035   1.0002
   0.500   0.7922   0.02383   0.01544  -0.0903   0.5930   1.0002
   0.750   0.8223   0.02362   0.01506  -0.0901   0.5855   1.0002
   1.000   0.8452   0.02402   0.01542  -0.0895   0.5752   1.0002
   1.250   0.8745   0.02393   0.01518  -0.0893   0.5672   1.0002
   1.500   0.8976   0.02439   0.01560  -0.0888   0.5572   1.0002
   1.750   0.9262   0.02440   0.01548  -0.0887   0.5489   1.0002
   2.000   0.9492   0.02486   0.01591  -0.0882   0.5389   1.0002
   2.250   0.9772   0.02494   0.01586  -0.0881   0.5305   1.0002
   2.500   1.0001   0.02545   0.01635  -0.0876   0.5211   1.0002
   2.750   1.0262   0.02572   0.01654  -0.0874   0.5129   1.0002
   3.000   1.0520   0.02614   0.01688  -0.0873   0.5053   1.0002
   3.250   1.0732   0.02671   0.01747  -0.0866   0.4963   1.0002
   3.500   1.1069   0.02668   0.01722  -0.0874   0.4907   1.0002
   3.750   1.1194   0.02776   0.01847  -0.0859   0.4810   1.0002
   4.000   1.1482   0.02796   0.01858  -0.0861   0.4750   1.0002
   4.250   1.1694   0.02872   0.01935  -0.0856   0.4684   1.0002
   4.500   1.1877   0.02949   0.02018  -0.0848   0.4610   1.0002
   4.750   1.2197   0.02956   0.02011  -0.0855   0.4559   1.0002
   5.000   1.2329   0.03070   0.02137  -0.0841   0.4490   1.0002
   5.250   1.2517   0.03148   0.02221  -0.0834   0.4429   1.0002
   5.500   1.2844   0.03156   0.02217  -0.0842   0.4382   1.0002
   5.750   1.2957   0.03281   0.02354  -0.0827   0.4321   1.0002
   6.000   1.3094   0.03381   0.02464  -0.0814   0.4260   1.0002
   6.250   1.3416   0.03388   0.02462  -0.0822   0.4213   1.0002
   6.500   1.3556   0.03489   0.02570  -0.0810   0.4154   1.0002
   6.750   1.3643   0.03589   0.02680  -0.0790   0.4085   1.0002
   7.000   1.4083   0.03516   0.02585  -0.0811   0.4028   1.0002
   7.250   1.4042   0.03687   0.02777  -0.0777   0.3963   1.0002
   7.500   1.4180   0.03761   0.02857  -0.0764   0.3902   1.0002
   7.750   1.4650   0.03704   0.02781  -0.0791   0.3853   1.0002
   8.000   1.4518   0.03923   0.03025  -0.0747   0.3799   1.0002
   8.250   1.4481   0.04081   0.03196  -0.0714   0.3744   1.0002
   8.500   1.4966   0.04019   0.03121  -0.0743   0.3692   1.0002
   8.750   1.4968   0.04178   0.03291  -0.0716   0.3644   1.0002
   9.000   1.4556   0.04531   0.03670  -0.0647   0.3593   1.0002
   9.250   1.4837   0.04544   0.03680  -0.0651   0.3541   1.0002
   9.500   1.5440   0.04441   0.03564  -0.0690   0.3490   1.0002
   9.750   1.2110   0.07645   0.06849  -0.0519   0.3344   1.0002
  10.000   1.3946   0.05821   0.05006  -0.0544   0.3376   1.0002
  10.250   1.5785   0.04761   0.03897  -0.0655   0.3327   1.0002
  10.750   1.2754   0.07985   0.07204  -0.0502   0.3155   1.0002
  11.000   1.3751   0.07032   0.06244  -0.0504   0.3146   1.0002
  11.250   0.9620   0.13793   0.13036  -0.0613   0.2670   1.0002
  11.500   1.0002   0.13521   0.12767  -0.0597   0.2656   1.0002
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