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AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AIRFOIL 3024 9.84% (s3024-il)
Reynolds number: 500,000
Max Cl/Cd: 96.8 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3024-il-500000-n5.txt
Download as CSV file: xf-s3024-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3658   0.11467   0.11231  -0.0316   1.0000   0.0104
 -10.750  -0.3615   0.11090   0.10855  -0.0331   1.0000   0.0104
 -10.500  -0.3599   0.10673   0.10441  -0.0346   1.0000   0.0105
 -10.250  -0.3531   0.10370   0.10139  -0.0360   1.0000   0.0104
  -9.750  -0.3466   0.09643   0.09417  -0.0388   1.0000   0.0104
  -9.250  -0.3256   0.08970   0.08745  -0.0442   0.9753   0.0095
  -9.000  -0.3140   0.08455   0.08228  -0.0495   0.9644   0.0089
  -8.750  -0.3045   0.07927   0.07698  -0.0549   0.9516   0.0089
  -8.500  -0.3057   0.07315   0.07084  -0.0595   0.9349   0.0082
  -8.250  -0.3075   0.06924   0.06690  -0.0617   0.9199   0.0083
  -8.000  -0.3250   0.06362   0.06126  -0.0648   0.9033   0.0080
  -7.500  -0.3618   0.03764   0.03475  -0.0801   0.8772   0.0073
  -7.250  -0.3634   0.02970   0.02613  -0.0811   0.8698   0.0074
  -7.000  -0.3526   0.02525   0.02109  -0.0809   0.8632   0.0076
  -6.750  -0.3350   0.02283   0.01833  -0.0805   0.8583   0.0078
  -6.500  -0.3138   0.02099   0.01621  -0.0801   0.8531   0.0080
  -6.250  -0.2916   0.01924   0.01414  -0.0797   0.8478   0.0081
  -6.000  -0.2686   0.01766   0.01223  -0.0791   0.8432   0.0081
  -5.750  -0.2441   0.01639   0.01073  -0.0787   0.8381   0.0082
  -5.500  -0.2190   0.01533   0.00945  -0.0783   0.8329   0.0083
  -5.250  -0.1936   0.01444   0.00837  -0.0779   0.8283   0.0085
  -5.000  -0.1677   0.01365   0.00745  -0.0775   0.8233   0.0087
  -4.750  -0.1415   0.01296   0.00664  -0.0772   0.8180   0.0090
  -4.500  -0.1153   0.01236   0.00592  -0.0769   0.8133   0.0093
  -4.250  -0.0887   0.01183   0.00530  -0.0766   0.8082   0.0097
  -4.000  -0.0620   0.01137   0.00476  -0.0764   0.8028   0.0101
  -3.750  -0.0352   0.01099   0.00429  -0.0761   0.7980   0.0104
  -3.500  -0.0085   0.01049   0.00374  -0.0760   0.7925   0.0111
  -3.250   0.0187   0.01019   0.00339  -0.0758   0.7869   0.0122
  -3.000   0.0459   0.00992   0.00305  -0.0756   0.7817   0.0128
  -2.750   0.0736   0.00967   0.00275  -0.0755   0.7755   0.0136
  -2.500   0.1010   0.00945   0.00245  -0.0753   0.7696   0.0150
  -2.250   0.1286   0.00924   0.00222  -0.0752   0.7634   0.0179
  -2.000   0.1557   0.00894   0.00202  -0.0751   0.7567   0.0427
  -1.750   0.1827   0.00863   0.00187  -0.0750   0.7502   0.0916
  -1.500   0.2098   0.00838   0.00176  -0.0749   0.7427   0.1395
  -1.250   0.2369   0.00816   0.00166  -0.0749   0.7357   0.1920
  -1.000   0.2635   0.00784   0.00160  -0.0748   0.7275   0.2798
  -0.750   0.2900   0.00755   0.00155  -0.0746   0.7193   0.3692
  -0.500   0.3157   0.00721   0.00151  -0.0744   0.7102   0.4828
  -0.250   0.3410   0.00688   0.00150  -0.0739   0.7004   0.5949
   0.000   0.3655   0.00660   0.00150  -0.0732   0.6901   0.6995
   0.250   0.3876   0.00629   0.00152  -0.0717   0.6794   0.8208
   0.500   0.4188   0.00614   0.00157  -0.0718   0.6675   0.9342
   0.750   0.4598   0.00618   0.00155  -0.0746   0.6543   0.9745
   1.000   0.4991   0.00625   0.00152  -0.0771   0.6401   0.9909
   1.250   0.5353   0.00634   0.00152  -0.0790   0.6251   1.0000
   1.500   0.5604   0.00645   0.00154  -0.0784   0.6100   1.0000
   1.750   0.5852   0.00658   0.00158  -0.0778   0.5938   1.0000
   2.000   0.6100   0.00673   0.00164  -0.0772   0.5768   1.0000
   2.250   0.6348   0.00688   0.00171  -0.0766   0.5597   1.0000
   2.500   0.6597   0.00705   0.00179  -0.0760   0.5417   1.0000
   2.750   0.6844   0.00723   0.00188  -0.0754   0.5228   1.0000
   3.000   0.7091   0.00743   0.00200  -0.0749   0.5039   1.0000
   3.250   0.7338   0.00763   0.00212  -0.0743   0.4845   1.0000
   3.500   0.7584   0.00785   0.00226  -0.0738   0.4637   1.0000
   4.000   0.8073   0.00834   0.00258  -0.0726   0.4213   1.0000
   4.500   0.8555   0.00890   0.00295  -0.0715   0.3769   1.0000
   4.750   0.8793   0.00920   0.00318  -0.0709   0.3556   1.0000
   5.000   0.9032   0.00950   0.00340  -0.0703   0.3340   1.0000
   5.250   0.9268   0.00983   0.00364  -0.0696   0.3128   1.0000
   5.500   0.9502   0.01017   0.00391  -0.0690   0.2914   1.0000
   5.750   0.9727   0.01058   0.00420  -0.0682   0.2660   1.0000
   6.000   0.9948   0.01102   0.00452  -0.0674   0.2393   1.0000
   6.250   1.0174   0.01141   0.00483  -0.0667   0.2174   1.0000
   6.500   1.0383   0.01194   0.00521  -0.0658   0.1877   1.0000
   6.750   1.0584   0.01251   0.00562  -0.0647   0.1573   1.0000
   7.000   1.0791   0.01302   0.00603  -0.0638   0.1350   1.0000
   7.250   1.0996   0.01355   0.00646  -0.0628   0.1152   1.0000
   7.500   1.1200   0.01405   0.00690  -0.0618   0.0988   1.0000
   7.750   1.1383   0.01470   0.00743  -0.0605   0.0768   1.0000
   8.000   1.1566   0.01533   0.00797  -0.0592   0.0588   1.0000
   8.250   1.1738   0.01601   0.00856  -0.0577   0.0428   1.0000
   8.500   1.1867   0.01696   0.00937  -0.0557   0.0202   1.0000
   8.750   1.2000   0.01777   0.01013  -0.0536   0.0114   1.0000
   9.000   1.2143   0.01841   0.01080  -0.0516   0.0097   1.0000
   9.250   1.2297   0.01897   0.01143  -0.0498   0.0092   1.0000
   9.500   1.2445   0.01958   0.01211  -0.0480   0.0087   1.0000
   9.750   1.2587   0.02026   0.01287  -0.0462   0.0083   1.0000
  10.000   1.2718   0.02102   0.01371  -0.0444   0.0080   1.0000
  10.250   1.2844   0.02184   0.01460  -0.0425   0.0077   1.0000
  10.500   1.2954   0.02279   0.01563  -0.0407   0.0074   1.0000
  10.750   1.3049   0.02386   0.01680  -0.0387   0.0072   1.0000
  11.000   1.3126   0.02510   0.01812  -0.0367   0.0070   1.0000
  11.250   1.3220   0.02623   0.01935  -0.0349   0.0069   1.0000
  11.500   1.3312   0.02741   0.02063  -0.0333   0.0068   1.0000
  11.750   1.3393   0.02870   0.02202  -0.0318   0.0066   1.0000
  12.000   1.3459   0.03017   0.02359  -0.0302   0.0064   1.0000
  12.250   1.3528   0.03163   0.02515  -0.0288   0.0062   1.0000
  12.500   1.3567   0.03344   0.02706  -0.0274   0.0061   1.0000
  12.750   1.3602   0.03533   0.02905  -0.0261   0.0061   1.0000
  13.000   1.3628   0.03738   0.03121  -0.0250   0.0059   1.0000
  13.250   1.3641   0.03965   0.03359  -0.0240   0.0058   1.0000
  13.500   1.3641   0.04214   0.03620  -0.0232   0.0057   1.0000
  13.750   1.3642   0.04473   0.03890  -0.0227   0.0057   1.0000
  14.000   1.3627   0.04760   0.04189  -0.0224   0.0056   1.0000
  14.250   1.3610   0.05064   0.04504  -0.0223   0.0055   1.0000
  14.500   1.3581   0.05398   0.04849  -0.0224   0.0055   1.0000
  14.750   1.3546   0.05753   0.05216  -0.0228   0.0054   1.0000
  15.000   1.3499   0.06142   0.05618  -0.0235   0.0054   1.0000
  15.250   1.3455   0.06544   0.06031  -0.0245   0.0053   1.0000
  15.500   1.3395   0.06982   0.06480  -0.0257   0.0052   1.0000
  15.750   1.3335   0.07434   0.06946  -0.0271   0.0052   1.0000
  16.000   1.3265   0.07920   0.07444  -0.0289   0.0052   1.0000
  16.250   1.3187   0.08429   0.07964  -0.0308   0.0051   1.0000
  16.500   1.3121   0.08934   0.08482  -0.0328   0.0051   1.0000
  16.750   1.3032   0.09487   0.09047  -0.0352   0.0050   1.0000
  17.000   1.2941   0.10057   0.09629  -0.0377   0.0050   1.0000
  17.250   1.2853   0.10633   0.10217  -0.0403   0.0049   1.0000
  17.500   1.2774   0.11203   0.10801  -0.0430   0.0049   1.0000
  17.750   1.2675   0.11817   0.11428  -0.0460   0.0049   1.0000
  18.000   1.2594   0.12417   0.12040  -0.0491   0.0049   1.0000
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