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EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 587 AIRFOIL (e587-il)
Reynolds number: 500,000
Max Cl/Cd: 109.96 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e587-il-500000-n5.txt
Download as CSV file: xf-e587-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3804   0.05414   0.05118  -0.1272   0.9393   0.0040
 -12.250  -0.3954   0.04364   0.04025  -0.1402   0.9307   0.0040
 -12.000  -0.3886   0.03710   0.03330  -0.1503   0.9203   0.0040
 -11.750  -0.3751   0.03265   0.02843  -0.1571   0.9059   0.0041
 -11.500  -0.3647   0.02974   0.02518  -0.1601   0.8888   0.0042
 -11.250  -0.3577   0.02777   0.02291  -0.1605   0.8732   0.0043
 -11.000  -0.3524   0.02620   0.02113  -0.1598   0.8596   0.0042
 -10.750  -0.3448   0.02495   0.01965  -0.1587   0.8483   0.0043
 -10.500  -0.3409   0.02351   0.01800  -0.1570   0.8376   0.0044
 -10.250  -0.3360   0.02227   0.01661  -0.1551   0.8288   0.0046
 -10.000  -0.3279   0.02134   0.01554  -0.1533   0.8211   0.0046
  -9.750  -0.3201   0.02059   0.01469  -0.1512   0.8139   0.0048
  -9.500  -0.3097   0.01991   0.01389  -0.1494   0.8071   0.0049
  -9.250  -0.2957   0.01912   0.01298  -0.1481   0.8015   0.0049
  -9.000  -0.2788   0.01855   0.01232  -0.1471   0.7963   0.0051
  -8.750  -0.2617   0.01790   0.01156  -0.1461   0.7912   0.0052
  -8.500  -0.2429   0.01733   0.01088  -0.1452   0.7867   0.0055
  -8.250  -0.2241   0.01673   0.01019  -0.1443   0.7821   0.0056
  -8.000  -0.2043   0.01617   0.00955  -0.1436   0.7776   0.0059
  -7.750  -0.1834   0.01566   0.00894  -0.1429   0.7738   0.0061
  -7.500  -0.1616   0.01520   0.00839  -0.1424   0.7702   0.0062
  -7.250  -0.1404   0.01466   0.00780  -0.1419   0.7662   0.0065
  -7.000  -0.1176   0.01424   0.00734  -0.1415   0.7622   0.0069
  -6.750  -0.0936   0.01391   0.00696  -0.1413   0.7587   0.0074
  -6.500  -0.0690   0.01358   0.00654  -0.1412   0.7556   0.0082
  -6.250  -0.0448   0.01319   0.00612  -0.1410   0.7523   0.0088
  -6.000  -0.0200   0.01283   0.00574  -0.1409   0.7486   0.0097
  -5.750   0.0055   0.01252   0.00537  -0.1408   0.7452   0.0108
  -5.500   0.0313   0.01220   0.00501  -0.1409   0.7421   0.0129
  -5.000   0.0842   0.01161   0.00442  -0.1412   0.7360   0.0238
  -4.750   0.1108   0.01132   0.00417  -0.1414   0.7326   0.0364
  -4.500   0.1379   0.01104   0.00395  -0.1417   0.7294   0.0531
  -4.250   0.1653   0.01074   0.00373  -0.1422   0.7264   0.0798
  -4.000   0.1931   0.01037   0.00351  -0.1428   0.7235   0.1256
  -3.750   0.2211   0.00990   0.00329  -0.1436   0.7204   0.1946
  -3.500   0.2498   0.00933   0.00304  -0.1447   0.7172   0.2920
  -3.250   0.2799   0.00864   0.00276  -0.1462   0.7139   0.4210
  -3.000   0.3098   0.00829   0.00274  -0.1472   0.7108   0.5332
  -2.750   0.3390   0.00829   0.00276  -0.1476   0.7079   0.5686
  -2.500   0.3678   0.00832   0.00278  -0.1479   0.7049   0.5874
  -2.250   0.3964   0.00836   0.00279  -0.1482   0.7015   0.5999
  -2.000   0.4251   0.00841   0.00280  -0.1485   0.6981   0.6113
  -1.750   0.4535   0.00849   0.00286  -0.1486   0.6948   0.6236
  -1.500   0.4819   0.00860   0.00294  -0.1488   0.6918   0.6356
  -1.250   0.5105   0.00868   0.00298  -0.1491   0.6886   0.6437
  -1.000   0.5387   0.00870   0.00298  -0.1493   0.6849   0.6470
  -0.750   0.5667   0.00873   0.00299  -0.1495   0.6813   0.6492
  -0.500   0.5949   0.00877   0.00299  -0.1497   0.6777   0.6514
  -0.250   0.6232   0.00881   0.00299  -0.1500   0.6743   0.6536
   0.000   0.6510   0.00884   0.00301  -0.1501   0.6702   0.6560
   0.250   0.6789   0.00887   0.00303  -0.1503   0.6660   0.6584
   0.500   0.7068   0.00892   0.00303  -0.1505   0.6618   0.6606
   0.750   0.7347   0.00898   0.00305  -0.1507   0.6579   0.6625
   1.000   0.7618   0.00900   0.00310  -0.1508   0.6532   0.6643
   1.250   0.7888   0.00905   0.00314  -0.1507   0.6483   0.6663
   1.750   0.8426   0.00916   0.00325  -0.1507   0.6384   0.6705
   2.000   0.8691   0.00922   0.00330  -0.1506   0.6327   0.6725
   2.250   0.8956   0.00930   0.00335  -0.1506   0.6276   0.6746
   2.500   0.9221   0.00936   0.00343  -0.1505   0.6218   0.6768
   2.750   0.9482   0.00945   0.00350  -0.1504   0.6157   0.6790
   3.000   0.9736   0.00953   0.00359  -0.1501   0.6096   0.6810
   3.250   0.9985   0.00960   0.00369  -0.1497   0.6021   0.6829
   3.500   1.0229   0.00971   0.00380  -0.1492   0.5947   0.6848
   3.750   1.0472   0.00981   0.00391  -0.1487   0.5864   0.6869
   4.000   1.0710   0.00994   0.00403  -0.1481   0.5786   0.6891
   4.250   1.0944   0.01007   0.00417  -0.1474   0.5696   0.6914
   4.500   1.1172   0.01021   0.00431  -0.1466   0.5608   0.6939
   4.750   1.1380   0.01038   0.00446  -0.1454   0.5504   0.6962
   5.000   1.1579   0.01053   0.00463  -0.1441   0.5392   0.6982
   5.250   1.1762   0.01072   0.00481  -0.1424   0.5273   0.7003
   5.500   1.1933   0.01095   0.00503  -0.1405   0.5146   0.7025
   5.750   1.2099   0.01124   0.00530  -0.1385   0.5005   0.7049
   6.000   1.2257   0.01157   0.00559  -0.1365   0.4855   0.7075
   6.250   1.2410   0.01193   0.00591  -0.1344   0.4701   0.7102
   6.500   1.2555   0.01233   0.00627  -0.1322   0.4537   0.7128
   6.750   1.2686   0.01277   0.00669  -0.1298   0.4362   0.7153
   7.000   1.2807   0.01327   0.00716  -0.1272   0.4179   0.7178
   7.250   1.2926   0.01381   0.00766  -0.1248   0.4004   0.7205
   7.500   1.3031   0.01442   0.00823  -0.1221   0.3822   0.7233
   7.750   1.3134   0.01509   0.00885  -0.1196   0.3647   0.7262
   8.250   1.3318   0.01661   0.01029  -0.1144   0.3297   0.7320
   8.500   1.3405   0.01746   0.01110  -0.1119   0.3125   0.7352
   8.750   1.3492   0.01835   0.01197  -0.1095   0.2952   0.7386
   9.000   1.3572   0.01934   0.01291  -0.1071   0.2774   0.7420
   9.500   1.3735   0.02143   0.01494  -0.1027   0.2445   0.7484
   9.750   1.3811   0.02257   0.01606  -0.1006   0.2287   0.7520
  10.000   1.3879   0.02381   0.01727  -0.0985   0.2124   0.7560
  10.250   1.3949   0.02510   0.01852  -0.0965   0.1968   0.7603
  10.500   1.4011   0.02648   0.01987  -0.0946   0.1805   0.7644
  10.750   1.4076   0.02789   0.02125  -0.0927   0.1656   0.7689
  11.000   1.4138   0.02937   0.02270  -0.0910   0.1513   0.7737
  11.500   1.4277   0.03234   0.02567  -0.0879   0.1269   0.7833
  11.750   1.4342   0.03394   0.02726  -0.0864   0.1160   0.7890
  12.000   1.4401   0.03563   0.02895  -0.0850   0.1050   0.7948
  12.250   1.4453   0.03740   0.03072  -0.0836   0.0939   0.8013
  12.500   1.4510   0.03919   0.03253  -0.0824   0.0839   0.8089
  12.750   1.4562   0.04106   0.03441  -0.0812   0.0740   0.8172
  13.250   1.4651   0.04505   0.03846  -0.0789   0.0572   0.8374
  13.500   1.4692   0.04712   0.04057  -0.0779   0.0503   0.8505
  13.750   1.4714   0.04941   0.04290  -0.0768   0.0428   0.8682
  14.000   1.4747   0.05139   0.04499  -0.0755   0.0380   0.9041
  14.250   1.4763   0.05350   0.04718  -0.0744   0.0334   1.0000
  14.500   1.4797   0.05601   0.04970  -0.0739   0.0290   1.0000
  14.750   1.4819   0.05870   0.05240  -0.0734   0.0241   1.0000
  15.000   1.4856   0.06129   0.05503  -0.0731   0.0212   1.0000
  15.250   1.4888   0.06399   0.05778  -0.0729   0.0184   1.0000
  15.500   1.4909   0.06685   0.06069  -0.0728   0.0157   1.0000
  15.750   1.4927   0.06982   0.06371  -0.0727   0.0137   1.0000
  16.000   1.4945   0.07287   0.06682  -0.0728   0.0117   1.0000
  16.250   1.4965   0.07593   0.06996  -0.0730   0.0104   1.0000
  16.500   1.4982   0.07910   0.07320  -0.0732   0.0093   1.0000
  16.750   1.4990   0.08245   0.07663  -0.0736   0.0083   1.0000
  17.000   1.4999   0.08582   0.08008  -0.0741   0.0074   1.0000
  17.250   1.4996   0.08940   0.08374  -0.0748   0.0066   1.0000
  17.500   1.4996   0.09301   0.08745  -0.0755   0.0060   1.0000
  17.750   1.4986   0.09682   0.09135  -0.0764   0.0054   1.0000
  18.000   1.4971   0.10075   0.09537  -0.0774   0.0050   1.0000
  18.250   1.4960   0.10464   0.09937  -0.0785   0.0046   1.0000
  18.500   1.4940   0.10873   0.10356  -0.0797   0.0042   1.0000
  18.750   1.4910   0.11301   0.10794  -0.0812   0.0039   1.0000
  19.000   1.4877   0.11738   0.11242  -0.0827   0.0036   1.0000
  19.250   1.4851   0.12167   0.11681  -0.0844   0.0034   1.0000
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