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EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 584 AIRFOIL (e584-il)
Reynolds number: 500,000
Max Cl/Cd: 103.12 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e584-il-500000.txt
Download as CSV file: xf-e584-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 584 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0544   0.09676   0.09334  -0.1203   0.7806   0.0196
 -11.500  -0.0618   0.09105   0.08761  -0.1235   0.7729   0.0197
 -11.250  -0.0596   0.08777   0.08430  -0.1241   0.7656   0.0199
 -11.000  -0.0514   0.08613   0.08260  -0.1239   0.7592   0.0202
 -10.750  -0.0493   0.08289   0.07936  -0.1251   0.7535   0.0203
 -10.500  -0.0449   0.08035   0.07679  -0.1258   0.7484   0.0205
 -10.250  -0.0443   0.07702   0.07343  -0.1272   0.7440   0.0207
 -10.000  -0.0444   0.07361   0.07004  -0.1287   0.7403   0.0213
  -9.750  -0.0488   0.06932   0.06577  -0.1309   0.7367   0.0214
  -9.500  -0.0596   0.06379   0.06026  -0.1348   0.7332   0.0216
  -9.250  -0.0815   0.05767   0.05408  -0.1387   0.7298   0.0214
  -9.000  -0.1025   0.05350   0.04981  -0.1387   0.7268   0.0216
  -8.750  -0.1209   0.05035   0.04661  -0.1366   0.7238   0.0218
  -8.500  -0.1401   0.04780   0.04396  -0.1328   0.7207   0.0221
  -8.250  -0.1913   0.04316   0.03863  -0.1243   0.7178   0.0236
  -8.000  -0.1855   0.03943   0.03490  -0.1233   0.7154   0.0239
  -7.750  -0.1748   0.03769   0.03310  -0.1220   0.7129   0.0242
  -7.500  -0.1646   0.03614   0.03148  -0.1205   0.7106   0.0246
  -7.250  -0.1545   0.03449   0.02973  -0.1188   0.7081   0.0252
  -7.000  -0.1451   0.03254   0.02757  -0.1166   0.7058   0.0265
  -6.500  -0.1380   0.02042   0.01375  -0.1069   0.7018   0.0130
  -6.250  -0.1152   0.01877   0.01190  -0.1061   0.6998   0.0126
  -6.000  -0.0906   0.01751   0.01043  -0.1056   0.6978   0.0122
  -5.750  -0.0656   0.01647   0.00923  -0.1051   0.6957   0.0120
  -5.500  -0.0416   0.01564   0.00832  -0.1044   0.6934   0.0120
  -5.250  -0.0182   0.01497   0.00759  -0.1037   0.6911   0.0122
  -5.000   0.0051   0.01441   0.00697  -0.1030   0.6889   0.0124
  -4.750   0.0282   0.01391   0.00642  -0.1022   0.6868   0.0129
  -4.500   0.0514   0.01347   0.00591  -0.1014   0.6845   0.0135
  -4.250   0.0748   0.01305   0.00546  -0.1008   0.6823   0.0149
  -4.000   0.0983   0.01271   0.00510  -0.1001   0.6801   0.0170
  -3.750   0.1219   0.01238   0.00478  -0.0995   0.6778   0.0212
  -3.500   0.1440   0.01191   0.00445  -0.0985   0.6754   0.0473
  -3.250   0.1671   0.01154   0.00427  -0.0980   0.6731   0.0913
  -3.000   0.1901   0.01117   0.00414  -0.0975   0.6708   0.1583
  -2.750   0.2100   0.01055   0.00401  -0.0967   0.6685   0.2962
  -2.500   0.2229   0.00941   0.00382  -0.0948   0.6663   0.5546
  -2.250   0.2371   0.00921   0.00446  -0.0915   0.6640   0.7778
  -2.000   0.2643   0.00952   0.00470  -0.0912   0.6615   0.8074
  -1.750   0.2908   0.00988   0.00500  -0.0905   0.6591   0.8213
  -1.500   0.3161   0.01029   0.00537  -0.0894   0.6568   0.8304
  -1.250   0.3430   0.01065   0.00564  -0.0890   0.6546   0.8409
  -1.000   0.3678   0.01110   0.00605  -0.0878   0.6523   0.8471
  -0.750   0.3930   0.01128   0.00620  -0.0872   0.6500   0.8552
  -0.500   0.4153   0.01149   0.00641  -0.0856   0.6475   0.8598
  -0.250   0.4381   0.01184   0.00674  -0.0840   0.6450   0.8693
   0.000   0.4592   0.01227   0.00717  -0.0813   0.6427   0.8801
   0.250   0.4839   0.01255   0.00739  -0.0801   0.6405   0.8902
   0.500   0.5138   0.01274   0.00752  -0.0804   0.6381   0.8933
   0.750   0.5362   0.01268   0.00748  -0.0795   0.6357   0.8964
   1.000   0.5587   0.01265   0.00745  -0.0788   0.6330   0.8996
   1.250   0.5832   0.01265   0.00742  -0.0787   0.6301   0.9023
   1.500   0.6091   0.01256   0.00730  -0.0785   0.6277   0.9037
   1.750   0.6372   0.01255   0.00723  -0.0788   0.6254   0.9048
   2.000   0.6630   0.01254   0.00722  -0.0786   0.6230   0.9060
   2.250   0.6854   0.01245   0.00717  -0.0778   0.6199   0.9076
   2.500   0.7099   0.01238   0.00710  -0.0774   0.6168   0.9087
   2.750   0.7360   0.01232   0.00703  -0.0774   0.6140   0.9101
   3.000   0.7640   0.01227   0.00694  -0.0778   0.6115   0.9111
   3.250   0.7903   0.01223   0.00691  -0.0779   0.6088   0.9120
   3.500   0.8131   0.01214   0.00687  -0.0773   0.6051   0.9135
   3.750   0.8387   0.01205   0.00679  -0.0772   0.6015   0.9144
   4.000   0.8664   0.01194   0.00667  -0.0776   0.5983   0.9151
   4.250   0.8939   0.01187   0.00659  -0.0780   0.5952   0.9157
   4.500   0.9177   0.01181   0.00659  -0.0776   0.5905   0.9168
   4.750   0.9441   0.01172   0.00653  -0.0778   0.5865   0.9173
   5.000   0.9704   0.01160   0.00640  -0.0778   0.5827   0.9178
   5.250   0.9937   0.01154   0.00638  -0.0773   0.5782   0.9184
   5.500   1.0167   0.01146   0.00635  -0.0767   0.5730   0.9190
   5.750   1.0415   0.01141   0.00628  -0.0764   0.5685   0.9196
   6.000   1.0634   0.01140   0.00631  -0.0756   0.5630   0.9207
   6.250   1.0855   0.01139   0.00634  -0.0748   0.5570   0.9215
   6.750   1.1305   0.01145   0.00645  -0.0736   0.5443   0.9229
   7.000   1.1523   0.01150   0.00650  -0.0729   0.5376   0.9236
   7.250   1.1708   0.01155   0.00659  -0.0714   0.5301   0.9246
   7.500   1.1896   0.01162   0.00668  -0.0701   0.5225   0.9255
   7.750   1.2082   0.01173   0.00684  -0.0688   0.5143   0.9265
   8.000   1.2261   0.01189   0.00700  -0.0674   0.5055   0.9275
   8.250   1.2430   0.01207   0.00722  -0.0658   0.4954   0.9290
   8.500   1.2594   0.01231   0.00746  -0.0643   0.4851   0.9300
   8.750   1.2743   0.01261   0.00775  -0.0625   0.4739   0.9310
   9.000   1.2884   0.01293   0.00810  -0.0606   0.4617   0.9320
   9.250   1.3000   0.01329   0.00846  -0.0583   0.4499   0.9334
   9.500   1.3095   0.01374   0.00892  -0.0558   0.4377   0.9349
   9.750   1.3174   0.01430   0.00946  -0.0531   0.4248   0.9366
  10.000   1.3240   0.01496   0.01011  -0.0504   0.4108   0.9384
  10.250   1.3310   0.01569   0.01085  -0.0479   0.3965   0.9404
  10.500   1.3362   0.01657   0.01172  -0.0453   0.3817   0.9424
  10.750   1.3397   0.01760   0.01274  -0.0427   0.3661   0.9447
  11.000   1.3423   0.01868   0.01382  -0.0401   0.3515   0.9475
  11.250   1.3433   0.01994   0.01506  -0.0374   0.3362   0.9505
  11.500   1.3441   0.02132   0.01644  -0.0350   0.3209   0.9537
  11.750   1.3444   0.02285   0.01795  -0.0327   0.3053   0.9573
  12.000   1.3452   0.02451   0.01959  -0.0308   0.2895   0.9616
  12.250   1.3460   0.02645   0.02149  -0.0294   0.2718   0.9673
  12.500   1.3501   0.02850   0.02351  -0.0290   0.2548   0.9753
  12.750   1.3521   0.03051   0.02549  -0.0281   0.2390   1.0000
  13.000   1.3541   0.03260   0.02755  -0.0272   0.2236   1.0000
  13.250   1.3574   0.03463   0.02955  -0.0264   0.2096   1.0000
  13.500   1.3608   0.03668   0.03159  -0.0257   0.1962   1.0000
  13.750   1.3629   0.03887   0.03374  -0.0250   0.1823   1.0000
  14.000   1.3656   0.04102   0.03588  -0.0244   0.1695   1.0000
  14.250   1.3670   0.04335   0.03818  -0.0238   0.1568   1.0000
  14.500   1.3688   0.04569   0.04049  -0.0232   0.1448   1.0000
  14.750   1.3691   0.04822   0.04298  -0.0227   0.1323   1.0000
  15.000   1.3690   0.05083   0.04557  -0.0223   0.1202   1.0000
  15.250   1.3687   0.05353   0.04822  -0.0220   0.1083   1.0000
  15.750   1.3694   0.05900   0.05367  -0.0217   0.0877   1.0000
  16.000   1.3702   0.06177   0.05643  -0.0217   0.0787   1.0000
  16.250   1.3701   0.06470   0.05937  -0.0217   0.0711   1.0000
  16.500   1.3689   0.06783   0.06249  -0.0218   0.0636   1.0000
  16.750   1.3690   0.07088   0.06556  -0.0221   0.0568   1.0000
  17.000   1.3686   0.07402   0.06872  -0.0225   0.0507   1.0000
  17.250   1.3668   0.07738   0.07210  -0.0229   0.0453   1.0000
  17.500   1.3635   0.08104   0.07577  -0.0235   0.0401   1.0000
  17.750   1.3621   0.08450   0.07927  -0.0242   0.0353   1.0000
  18.000   1.3604   0.08805   0.08287  -0.0249   0.0317   1.0000
  18.250   1.3554   0.09210   0.08693  -0.0259   0.0282   1.0000
  18.500   1.3549   0.09561   0.09053  -0.0269   0.0257   1.0000
  18.750   1.3513   0.09960   0.09457  -0.0280   0.0231   1.0000
  19.000   1.3490   0.10347   0.09849  -0.0293   0.0207   1.0000
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