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EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 587 AIRFOIL (e587-il)
Reynolds number: 500,000
Max Cl/Cd: 116.36 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e587-il-500000.txt
Download as CSV file: xf-e587-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 587 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2345   0.03001   0.02565  -0.1605   0.8707   0.0106
  -9.250  -0.2337   0.02799   0.02341  -0.1585   0.8611   0.0103
  -9.000  -0.2319   0.02518   0.02018  -0.1563   0.8531   0.0099
  -8.750  -0.2255   0.02266   0.01727  -0.1541   0.8456   0.0095
  -8.500  -0.2102   0.02105   0.01538  -0.1528   0.8395   0.0097
  -8.250  -0.1910   0.01975   0.01383  -0.1520   0.8345   0.0099
  -8.000  -0.1725   0.01873   0.01262  -0.1508   0.8291   0.0104
  -7.750  -0.1515   0.01788   0.01160  -0.1500   0.8242   0.0107
  -7.500  -0.1276   0.01725   0.01078  -0.1497   0.8199   0.0109
  -7.250  -0.1102   0.01616   0.00968  -0.1484   0.8151   0.0113
  -7.000  -0.0897   0.01553   0.00902  -0.1476   0.8106   0.0117
  -6.750  -0.0671   0.01499   0.00843  -0.1472   0.8066   0.0122
  -6.500  -0.0432   0.01454   0.00789  -0.1470   0.8028   0.0131
  -6.250  -0.0220   0.01404   0.00736  -0.1462   0.7985   0.0141
  -6.000   0.0007   0.01354   0.00685  -0.1459   0.7944   0.0153
  -5.750   0.0256   0.01315   0.00638  -0.1458   0.7909   0.0168
  -5.250   0.0749   0.01215   0.00534  -0.1456   0.7837   0.0252
  -5.000   0.0995   0.01158   0.00489  -0.1456   0.7798   0.0468
  -4.750   0.1260   0.01113   0.00458  -0.1460   0.7764   0.0821
  -4.500   0.1537   0.01066   0.00429  -0.1467   0.7732   0.1362
  -4.250   0.1811   0.00994   0.00399  -0.1478   0.7699   0.2470
  -4.000   0.2090   0.00866   0.00359  -0.1497   0.7663   0.4855
  -3.750   0.2378   0.00857   0.00370  -0.1501   0.7629   0.5710
  -3.500   0.2673   0.00865   0.00373  -0.1505   0.7596   0.5974
  -3.250   0.2974   0.00878   0.00377  -0.1509   0.7566   0.6135
  -3.000   0.3260   0.00893   0.00388  -0.1511   0.7534   0.6267
  -2.750   0.3533   0.00905   0.00399  -0.1509   0.7498   0.6364
  -2.500   0.3823   0.00917   0.00402  -0.1512   0.7463   0.6457
  -2.250   0.4105   0.00926   0.00411  -0.1513   0.7432   0.6519
  -2.000   0.4403   0.00942   0.00419  -0.1517   0.7401   0.6598
  -1.750   0.4673   0.00957   0.00435  -0.1514   0.7368   0.6675
  -1.500   0.4942   0.00973   0.00451  -0.1512   0.7332   0.6757
  -1.250   0.5222   0.00980   0.00455  -0.1513   0.7296   0.6814
  -1.000   0.5504   0.00986   0.00459  -0.1514   0.7264   0.6850
  -0.750   0.5805   0.00995   0.00461  -0.1520   0.7232   0.6881
  -0.500   0.6074   0.00995   0.00461  -0.1520   0.7195   0.6910
  -0.250   0.6357   0.00996   0.00459  -0.1523   0.7156   0.6938
   0.000   0.6648   0.00996   0.00453  -0.1528   0.7118   0.6963
   0.250   0.6938   0.00996   0.00450  -0.1532   0.7084   0.6982
   0.500   0.7213   0.00999   0.00454  -0.1533   0.7046   0.7001
   0.750   0.7479   0.01000   0.00456  -0.1533   0.7003   0.7023
   1.000   0.7759   0.01001   0.00456  -0.1535   0.6962   0.7047
   1.250   0.8053   0.01004   0.00454  -0.1540   0.6924   0.7071
   1.500   0.8326   0.01008   0.00457  -0.1541   0.6880   0.7095
   1.750   0.8597   0.01009   0.00459  -0.1542   0.6831   0.7118
   2.000   0.8873   0.01007   0.00456  -0.1543   0.6787   0.7139
   2.250   0.9159   0.01012   0.00459  -0.1547   0.6746   0.7160
   2.500   0.9407   0.01013   0.00467  -0.1542   0.6695   0.7181
   2.750   0.9672   0.01015   0.00470  -0.1542   0.6644   0.7203
   3.000   0.9959   0.01021   0.00471  -0.1545   0.6597   0.7226
   3.250   1.0203   0.01023   0.00479  -0.1541   0.6537   0.7251
   3.500   1.0464   0.01026   0.00482  -0.1539   0.6478   0.7277
   3.750   1.0735   0.01031   0.00485  -0.1540   0.6423   0.7300
   4.000   1.0970   0.01033   0.00495  -0.1533   0.6358   0.7322
   4.250   1.1226   0.01038   0.00500  -0.1530   0.6296   0.7343
   4.500   1.1465   0.01044   0.00512  -0.1525   0.6228   0.7367
   4.750   1.1705   0.01051   0.00520  -0.1519   0.6153   0.7393
   5.000   1.1941   0.01059   0.00530  -0.1513   0.6076   0.7420
   5.250   1.2173   0.01069   0.00540  -0.1506   0.5992   0.7448
   5.500   1.2392   0.01077   0.00553  -0.1496   0.5904   0.7473
   5.750   1.2604   0.01090   0.00565  -0.1484   0.5813   0.7498
   6.000   1.2800   0.01101   0.00582  -0.1470   0.5706   0.7525
   6.250   1.2986   0.01116   0.00599  -0.1454   0.5602   0.7553
   6.500   1.3147   0.01134   0.00616  -0.1433   0.5488   0.7584
   6.750   1.3303   0.01156   0.00637  -0.1411   0.5359   0.7614
   7.000   1.3453   0.01180   0.00663  -0.1388   0.5223   0.7644
   7.250   1.3592   0.01210   0.00695  -0.1364   0.5079   0.7676
   7.500   1.3720   0.01247   0.00730  -0.1338   0.4920   0.7711
   7.750   1.3837   0.01290   0.00770  -0.1311   0.4754   0.7747
   8.000   1.3938   0.01342   0.00817  -0.1283   0.4574   0.7782
   8.250   1.4020   0.01399   0.00872  -0.1251   0.4392   0.7816
   8.500   1.4101   0.01462   0.00933  -0.1221   0.4193   0.7854
   8.750   1.4169   0.01537   0.01004  -0.1189   0.3993   0.7899
   9.000   1.4232   0.01622   0.01082  -0.1159   0.3801   0.7943
   9.250   1.4273   0.01716   0.01173  -0.1126   0.3608   0.7987
   9.500   1.4332   0.01813   0.01267  -0.1098   0.3413   0.8034
   9.750   1.4385   0.01921   0.01371  -0.1070   0.3215   0.8086
  10.000   1.4427   0.02038   0.01484  -0.1042   0.3025   0.8136
  10.250   1.4461   0.02167   0.01609  -0.1015   0.2835   0.8194
  10.500   1.4504   0.02302   0.01739  -0.0990   0.2646   0.8260
  10.750   1.4551   0.02433   0.01870  -0.0967   0.2471   0.8328
  11.000   1.4601   0.02573   0.02008  -0.0946   0.2305   0.8410
  11.250   1.4641   0.02719   0.02154  -0.0924   0.2143   0.8497
  11.500   1.4683   0.02871   0.02305  -0.0903   0.1987   0.8604
  11.750   1.4718   0.03028   0.02462  -0.0883   0.1834   0.8744
  12.000   1.4744   0.03182   0.02620  -0.0860   0.1691   0.8974
  12.250   1.4752   0.03335   0.02778  -0.0837   0.1553   1.0000
  12.500   1.4799   0.03527   0.02964  -0.0825   0.1407   1.0000
  12.750   1.4844   0.03723   0.03156  -0.0813   0.1269   1.0000
  13.000   1.4886   0.03926   0.03354  -0.0801   0.1141   1.0000
  13.250   1.4918   0.04142   0.03566  -0.0790   0.1015   1.0000
  13.500   1.4953   0.04361   0.03782  -0.0779   0.0904   1.0000
  13.750   1.4974   0.04598   0.04013  -0.0769   0.0785   1.0000
  14.000   1.4998   0.04839   0.04253  -0.0761   0.0695   1.0000
  14.250   1.5014   0.05095   0.04507  -0.0752   0.0604   1.0000
  14.500   1.5032   0.05354   0.04764  -0.0746   0.0523   1.0000
  14.750   1.5040   0.05631   0.05040  -0.0740   0.0446   1.0000
  15.000   1.5064   0.05899   0.05311  -0.0735   0.0392   1.0000
  15.250   1.5076   0.06185   0.05599  -0.0731   0.0341   1.0000
  15.500   1.5075   0.06495   0.05910  -0.0729   0.0297   1.0000
  15.750   1.5084   0.06798   0.06217  -0.0727   0.0262   1.0000
  16.000   1.5094   0.07106   0.06531  -0.0727   0.0230   1.0000
  16.250   1.5081   0.07451   0.06880  -0.0728   0.0206   1.0000
  16.500   1.5093   0.07774   0.07211  -0.0730   0.0185   1.0000
  16.750   1.5073   0.08143   0.07586  -0.0734   0.0167   1.0000
  17.000   1.5076   0.08485   0.07937  -0.0739   0.0151   1.0000
  17.250   1.5037   0.08896   0.08354  -0.0745   0.0138   1.0000
  17.500   1.5033   0.09263   0.08733  -0.0752   0.0125   1.0000
  17.750   1.4996   0.09686   0.09163  -0.0762   0.0115   1.0000
  18.000   1.4959   0.10114   0.09602  -0.0773   0.0105   1.0000
  18.250   1.4929   0.10535   0.10033  -0.0784   0.0096   1.0000
  18.500   1.4867   0.11014   0.10521  -0.0799   0.0089   1.0000
  18.750   1.4824   0.11467   0.10986  -0.0815   0.0083   1.0000
  19.000   1.4788   0.11914   0.11443  -0.0831   0.0076   1.0000
  19.250   1.4725   0.12409   0.11947  -0.0851   0.0071   1.0000
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