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AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AIRFOIL 3024 9.84% (s3024-il)
Reynolds number: 50,000
Max Cl/Cd: 34.4 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3024-il-50000.txt
Download as CSV file: xf-s3024-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL 3024    9.84%                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3355   0.10218   0.09577  -0.0299   1.0000   0.2178
  -8.000  -0.3360   0.10012   0.09379  -0.0284   1.0000   0.2273
  -7.750  -0.3379   0.09753   0.09131  -0.0268   1.0000   0.2346
  -7.500  -0.3532   0.09678   0.09070  -0.0244   1.0000   0.2431
  -7.250  -0.3538   0.09407   0.08807  -0.0220   1.0000   0.2502
  -7.000  -0.3727   0.09351   0.08765  -0.0186   1.0000   0.2576
  -6.750  -0.4097   0.09416   0.08850  -0.0157   1.0000   0.2598
  -6.500  -0.3988   0.09061   0.08497  -0.0123   1.0000   0.2725
  -6.250  -0.4033   0.08818   0.08263  -0.0096   1.0000   0.2817
  -6.000  -0.4360   0.08825   0.08284  -0.0090   1.0000   0.2902
  -5.750  -0.4297   0.08509   0.07972  -0.0054   1.0000   0.3037
  -5.500  -0.4290   0.08242   0.07711  -0.0024   1.0000   0.3155
  -5.250  -0.4344   0.08016   0.07492   0.0000   1.0000   0.3298
  -5.000  -0.4400   0.07801   0.07284   0.0022   1.0000   0.3466
  -4.750  -0.4513   0.07622   0.07112   0.0034   1.0000   0.3673
  -4.500  -0.4460   0.07339   0.06835   0.0076   1.0000   0.3860
  -3.500  -0.3181   0.04316   0.03535  -0.0397   1.0000   0.1232
  -3.250  -0.2931   0.03978   0.03150  -0.0404   1.0000   0.1174
  -3.000  -0.2674   0.03704   0.02821  -0.0407   1.0000   0.1166
  -2.750  -0.2428   0.03496   0.02568  -0.0406   1.0000   0.1184
  -2.500  -0.2176   0.03304   0.02331  -0.0403   1.0000   0.1200
  -2.250  -0.1921   0.03139   0.02116  -0.0398   1.0000   0.1234
  -2.000  -0.1686   0.03005   0.01967  -0.0393   1.0000   0.1343
  -1.750  -0.1446   0.02893   0.01839  -0.0386   1.0000   0.1507
  -1.500  -0.1206   0.02788   0.01732  -0.0379   1.0000   0.1860
  -1.250  -0.0924   0.02633   0.01638  -0.0379   1.0000   0.3045
  -1.000  -0.0651   0.02289   0.01537  -0.0358   1.0000   1.0000
  -0.750  -0.0442   0.02338   0.01526  -0.0355   1.0000   1.0000
  -0.500  -0.0243   0.02391   0.01536  -0.0351   1.0000   1.0000
  -0.250  -0.0050   0.02449   0.01556  -0.0348   1.0000   1.0000
   0.000   0.0140   0.02511   0.01588  -0.0346   1.0000   1.0000
   0.250   0.0327   0.02578   0.01629  -0.0343   1.0000   1.0000
   0.500   0.0658   0.02690   0.01712  -0.0369   0.9940   1.0000
   0.750   0.1103   0.02828   0.01820  -0.0415   0.9804   1.0000
   1.000   0.1523   0.02960   0.01930  -0.0456   0.9663   1.0000
   1.250   0.1922   0.03085   0.02036  -0.0492   0.9520   1.0000
   1.500   0.2307   0.03205   0.02139  -0.0524   0.9372   1.0000
   1.750   0.2678   0.03320   0.02242  -0.0552   0.9222   1.0000
   2.000   0.3042   0.03431   0.02343  -0.0578   0.9067   1.0000
   2.250   0.3395   0.03537   0.02442  -0.0601   0.8913   1.0000
   2.500   0.3757   0.03639   0.02539  -0.0623   0.8753   1.0000
   2.750   0.4123   0.03736   0.02633  -0.0645   0.8592   1.0000
   3.000   0.4498   0.03825   0.02722  -0.0666   0.8431   1.0000
   3.250   0.4794   0.03908   0.02805  -0.0674   0.8262   1.0000
   3.500   0.5061   0.03989   0.02888  -0.0678   0.8087   1.0000
   3.750   0.5363   0.04064   0.02969  -0.0685   0.7913   1.0000
   4.000   0.5694   0.04129   0.03040  -0.0694   0.7742   1.0000
   4.250   0.6051   0.04179   0.03097  -0.0704   0.7575   1.0000
   4.500   0.6444   0.04206   0.03138  -0.0716   0.7409   1.0000
   4.750   0.6710   0.04260   0.03200  -0.0712   0.7228   1.0000
   5.000   0.6962   0.04311   0.03262  -0.0706   0.7038   1.0000
   5.250   0.7322   0.04310   0.03275  -0.0708   0.6863   1.0000
   5.500   0.7749   0.04253   0.03240  -0.0712   0.6695   1.0000
   5.750   0.8256   0.04117   0.03127  -0.0717   0.6535   1.0000
   6.000   0.8495   0.04127   0.03154  -0.0701   0.6336   1.0000
   6.250   0.8881   0.04020   0.03068  -0.0691   0.6152   1.0000
   6.500   0.9414   0.03790   0.02861  -0.0688   0.5974   1.0000
   6.750   0.9870   0.03609   0.02705  -0.0679   0.5767   1.0000
   7.000   1.0297   0.03453   0.02564  -0.0669   0.5530   1.0000
   7.250   1.0616   0.03390   0.02516  -0.0653   0.5266   1.0000
   7.500   1.0938   0.03337   0.02469  -0.0637   0.4986   1.0000
   7.750   1.1223   0.03325   0.02460  -0.0621   0.4693   1.0000
   8.000   1.1474   0.03350   0.02485  -0.0603   0.4396   1.0000
   8.250   1.1701   0.03401   0.02537  -0.0584   0.4096   1.0000
   8.500   1.1907   0.03479   0.02613  -0.0564   0.3802   1.0000
   8.750   1.2095   0.03581   0.02714  -0.0544   0.3516   1.0000
   9.000   1.2266   0.03697   0.02829  -0.0523   0.3234   1.0000
   9.250   1.2427   0.03830   0.02960  -0.0502   0.2962   1.0000
   9.500   1.2580   0.03973   0.03101  -0.0481   0.2692   1.0000
   9.750   1.2716   0.04126   0.03246  -0.0458   0.2421   1.0000
  10.000   1.2800   0.04272   0.03382  -0.0430   0.2143   1.0000
  10.250   1.2806   0.04379   0.03470  -0.0396   0.1869   1.0000
  10.500   1.2726   0.04535   0.03637  -0.0355   0.1648   1.0000
  10.750   1.2707   0.04747   0.03837  -0.0322   0.1427   1.0000
  11.000   1.2688   0.05010   0.04103  -0.0290   0.1250   1.0000
  11.250   1.2700   0.05300   0.04400  -0.0263   0.1118   1.0000
  11.500   1.2744   0.05648   0.04766  -0.0243   0.1029   1.0000
  11.750   1.2780   0.06001   0.05143  -0.0224   0.0970   1.0000
  12.000   1.2815   0.06409   0.05566  -0.0209   0.0928   1.0000
  12.250   1.2647   0.06792   0.05989  -0.0183   0.0919   1.0000
  12.500   1.2449   0.07222   0.06454  -0.0165   0.0912   1.0000
  12.750   1.2230   0.07696   0.06957  -0.0156   0.0911   1.0000
  13.000   1.1993   0.08223   0.07510  -0.0156   0.0914   1.0000
  13.250   1.1738   0.08821   0.08129  -0.0166   0.0920   1.0000
  13.500   1.1477   0.09490   0.08816  -0.0187   0.0927   1.0000
  13.750   1.1247   0.10209   0.09548  -0.0215   0.0935   1.0000
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