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AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AIRFOIL 3024 9.84% (s3024-il)
Reynolds number: 50,000
Max Cl/Cd: 38.27 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3024-il-50000-n5.txt
Download as CSV file: xf-s3024-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3482   0.10787   0.10115  -0.0379   1.0000   0.1146
  -8.750  -0.3598   0.10615   0.09959  -0.0395   1.0000   0.1152
  -8.500  -0.3712   0.10425   0.09783  -0.0399   1.0000   0.1154
  -8.000  -0.3584   0.09193   0.08548  -0.0397   1.0000   0.0582
  -7.750  -0.3665   0.08972   0.08339  -0.0378   1.0000   0.0565
  -7.500  -0.3804   0.08792   0.08170  -0.0357   1.0000   0.0552
  -7.250  -0.3942   0.08553   0.07942  -0.0346   1.0000   0.0537
  -6.750  -0.4244   0.07723   0.07117  -0.0390   1.0000   0.0479
  -6.500  -0.4270   0.07451   0.06848  -0.0376   1.0000   0.0473
  -6.250  -0.4290   0.07150   0.06547  -0.0370   1.0000   0.0466
  -6.000  -0.4293   0.06823   0.06216  -0.0368   1.0000   0.0459
  -5.750  -0.4174   0.06375   0.05753  -0.0396   0.9966   0.0450
  -5.500  -0.3948   0.05824   0.05174  -0.0447   0.9900   0.0439
  -5.250  -0.3695   0.05289   0.04601  -0.0494   0.9840   0.0430
  -5.000  -0.3442   0.04799   0.04062  -0.0528   0.9776   0.0423
  -4.750  -0.3147   0.04362   0.03568  -0.0559   0.9724   0.0420
  -4.500  -0.2878   0.04031   0.03183  -0.0576   0.9662   0.0431
  -4.250  -0.2552   0.03728   0.02817  -0.0597   0.9612   0.0452
  -4.000  -0.2256   0.03482   0.02503  -0.0605   0.9555   0.0471
  -3.750  -0.1936   0.03262   0.02229  -0.0614   0.9502   0.0486
  -3.500  -0.1587   0.03081   0.02025  -0.0631   0.9460   0.0511
  -3.250  -0.1321   0.02956   0.01878  -0.0629   0.9392   0.0547
  -3.000  -0.0980   0.02839   0.01732  -0.0639   0.9341   0.0621
  -2.750  -0.0660   0.02741   0.01612  -0.0646   0.9284   0.0730
  -2.500  -0.0355   0.02649   0.01524  -0.0653   0.9220   0.0963
  -2.250   0.0014   0.02528   0.01443  -0.0675   0.9175   0.1776
  -2.000   0.0259   0.02420   0.01401  -0.0675   0.9100   0.3158
  -1.750   0.0519   0.02297   0.01391  -0.0670   0.9045   0.5664
  -1.500   0.1176   0.02215   0.01359  -0.0724   0.9027   1.0000
  -1.250   0.1416   0.02238   0.01340  -0.0720   0.8932   1.0000
  -1.000   0.1810   0.02257   0.01320  -0.0744   0.8875   1.0000
  -0.750   0.2034   0.02283   0.01316  -0.0737   0.8774   1.0000
  -0.500   0.2381   0.02303   0.01308  -0.0751   0.8707   1.0000
  -0.250   0.2637   0.02328   0.01310  -0.0748   0.8611   1.0000
   0.000   0.2919   0.02352   0.01314  -0.0750   0.8525   1.0000
   0.250   0.3234   0.02370   0.01313  -0.0757   0.8444   1.0000
   0.500   0.3477   0.02397   0.01326  -0.0752   0.8343   1.0000
   0.750   0.3835   0.02406   0.01321  -0.0764   0.8276   1.0000
   1.000   0.4053   0.02435   0.01339  -0.0755   0.8162   1.0000
   1.250   0.4316   0.02456   0.01351  -0.0751   0.8063   1.0000
   1.500   0.4647   0.02461   0.01349  -0.0758   0.7984   1.0000
   1.750   0.4873   0.02487   0.01369  -0.0748   0.7867   1.0000
   2.000   0.5131   0.02504   0.01383  -0.0743   0.7761   1.0000
   2.250   0.5473   0.02496   0.01371  -0.0748   0.7681   1.0000
   2.500   0.5699   0.02517   0.01393  -0.0738   0.7556   1.0000
   2.750   0.5943   0.02532   0.01408  -0.0729   0.7435   1.0000
   3.000   0.6206   0.02539   0.01416  -0.0723   0.7319   1.0000
   3.250   0.6514   0.02527   0.01406  -0.0721   0.7219   1.0000
   3.500   0.6784   0.02525   0.01411  -0.0714   0.7098   1.0000
   3.750   0.7028   0.02533   0.01423  -0.0705   0.6964   1.0000
   4.000   0.7279   0.02537   0.01433  -0.0695   0.6827   1.0000
   4.250   0.7533   0.02538   0.01444  -0.0686   0.6688   1.0000
   4.500   0.7791   0.02537   0.01449  -0.0676   0.6544   1.0000
   4.750   0.8051   0.02534   0.01454  -0.0667   0.6394   1.0000
   5.000   0.8314   0.02529   0.01457  -0.0657   0.6238   1.0000
   5.250   0.8581   0.02522   0.01461  -0.0648   0.6074   1.0000
   5.500   0.8835   0.02523   0.01469  -0.0637   0.5897   1.0000
   5.750   0.9059   0.02540   0.01495  -0.0624   0.5697   1.0000
   6.000   0.9311   0.02546   0.01511  -0.0613   0.5498   1.0000
   6.250   0.9546   0.02563   0.01534  -0.0600   0.5285   1.0000
   6.500   0.9769   0.02590   0.01566  -0.0587   0.5059   1.0000
   6.750   0.9984   0.02625   0.01606  -0.0573   0.4828   1.0000
   7.000   1.0195   0.02664   0.01650  -0.0558   0.4592   1.0000
   7.250   1.0379   0.02720   0.01713  -0.0542   0.4348   1.0000
   7.500   1.0567   0.02778   0.01771  -0.0526   0.4111   1.0000
   7.750   1.0735   0.02847   0.01844  -0.0508   0.3869   1.0000
   8.000   1.0894   0.02926   0.01929  -0.0491   0.3634   1.0000
   8.250   1.1049   0.03008   0.02012  -0.0473   0.3409   1.0000
   8.500   1.1182   0.03104   0.02115  -0.0453   0.3183   1.0000
   8.750   1.1314   0.03203   0.02215  -0.0434   0.2974   1.0000
   9.000   1.1427   0.03313   0.02332  -0.0414   0.2768   1.0000
   9.250   1.1522   0.03428   0.02457  -0.0392   0.2574   1.0000
   9.500   1.1610   0.03551   0.02581  -0.0370   0.2393   1.0000
   9.750   1.1683   0.03687   0.02723  -0.0348   0.2215   1.0000
  10.000   1.1745   0.03835   0.02883  -0.0327   0.2042   1.0000
  10.250   1.1789   0.03996   0.03052  -0.0306   0.1875   1.0000
  10.500   1.1821   0.04172   0.03234  -0.0287   0.1716   1.0000
  10.750   1.1824   0.04369   0.03434  -0.0268   0.1560   1.0000
  11.000   1.1793   0.04592   0.03661  -0.0251   0.1407   1.0000
  11.250   1.1733   0.04853   0.03927  -0.0239   0.1241   1.0000
  11.500   1.1677   0.05138   0.04218  -0.0230   0.1087   1.0000
  11.750   1.1612   0.05458   0.04541  -0.0225   0.0941   1.0000
  12.000   1.1558   0.05798   0.04885  -0.0222   0.0828   1.0000
  12.250   1.1501   0.06159   0.05247  -0.0221   0.0744   1.0000
  12.500   1.1440   0.06547   0.05643  -0.0222   0.0663   1.0000
  12.750   1.1395   0.06937   0.06047  -0.0224   0.0602   1.0000
  13.000   1.1340   0.07341   0.06457  -0.0228   0.0556   1.0000
  13.250   1.1307   0.07740   0.06868  -0.0232   0.0523   1.0000
  13.500   1.1279   0.08159   0.07312  -0.0236   0.0490   1.0000
  13.750   1.1247   0.08577   0.07744  -0.0244   0.0468   1.0000
  14.000   1.1218   0.08986   0.08158  -0.0253   0.0449   1.0000
  14.250   1.1170   0.09470   0.08663  -0.0266   0.0434   1.0000
  14.500   1.1088   0.10044   0.09270  -0.0286   0.0423   1.0000
  14.750   1.0979   0.10687   0.09940  -0.0315   0.0414   1.0000
  15.000   1.0850   0.11400   0.10676  -0.0349   0.0410   1.0000
  15.250   1.0692   0.12220   0.11519  -0.0393   0.0409   1.0000
  15.500   1.0499   0.13183   0.12502  -0.0447   0.0413   1.0000
  15.750   1.0269   0.14330   0.13663  -0.0515   0.0420   1.0000
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