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EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 587 AIRFOIL (e587-il)
Reynolds number: 200,000
Max Cl/Cd: 75.85 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e587-il-200000-n5.txt
Download as CSV file: xf-e587-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1842   0.08943   0.08570  -0.1059   0.9370   0.0104
 -11.000  -0.1842   0.08213   0.07841  -0.1118   0.9325   0.0100
 -10.750  -0.2302   0.06070   0.05683  -0.1280   0.9251   0.0094
 -10.500  -0.2648   0.04809   0.04373  -0.1410   0.9158   0.0091
 -10.250  -0.2766   0.04230   0.03755  -0.1459   0.9040   0.0091
 -10.000  -0.2816   0.03809   0.03294  -0.1484   0.8929   0.0091
  -9.750  -0.2793   0.03505   0.02956  -0.1496   0.8834   0.0093
  -9.500  -0.2800   0.03323   0.02748  -0.1482   0.8724   0.0095
  -9.250  -0.2743   0.03090   0.02478  -0.1475   0.8646   0.0096
  -9.000  -0.2646   0.02931   0.02286  -0.1464   0.8570   0.0104
  -8.750  -0.2483   0.02734   0.02044  -0.1461   0.8518   0.0108
  -8.500  -0.2358   0.02628   0.01926  -0.1446   0.8447   0.0114
  -8.250  -0.2163   0.02514   0.01794  -0.1443   0.8393   0.0117
  -8.000  -0.1945   0.02390   0.01649  -0.1440   0.8350   0.0121
  -7.750  -0.1772   0.02288   0.01534  -0.1427   0.8294   0.0124
  -7.500  -0.1565   0.02192   0.01422  -0.1420   0.8245   0.0128
  -7.250  -0.1334   0.02095   0.01308  -0.1417   0.8206   0.0133
  -7.000  -0.1149   0.02020   0.01223  -0.1405   0.8156   0.0138
  -6.750  -0.0962   0.01950   0.01151  -0.1396   0.8108   0.0144
  -6.500  -0.0744   0.01884   0.01077  -0.1392   0.8068   0.0155
  -6.250  -0.0501   0.01820   0.00998  -0.1392   0.8035   0.0168
  -6.000  -0.0312   0.01774   0.00953  -0.1381   0.7985   0.0188
  -5.750  -0.0091   0.01726   0.00901  -0.1377   0.7942   0.0221
  -5.500   0.0149   0.01671   0.00840  -0.1375   0.7907   0.0268
  -5.250   0.0414   0.01619   0.00783  -0.1379   0.7877   0.0356
  -5.000   0.0629   0.01573   0.00745  -0.1373   0.7833   0.0510
  -4.750   0.0865   0.01526   0.00708  -0.1372   0.7792   0.0769
  -4.500   0.1120   0.01472   0.00671  -0.1376   0.7757   0.1219
  -4.250   0.1393   0.01400   0.00630  -0.1387   0.7727   0.2032
  -4.000   0.1655   0.01305   0.00590  -0.1399   0.7692   0.3442
  -3.750   0.1894   0.01252   0.00607  -0.1398   0.7651   0.5171
  -3.500   0.2162   0.01266   0.00627  -0.1394   0.7616   0.5724
  -3.250   0.2452   0.01281   0.00633  -0.1396   0.7584   0.5999
  -3.000   0.2751   0.01298   0.00638  -0.1399   0.7557   0.6182
  -2.750   0.3011   0.01315   0.00648  -0.1395   0.7518   0.6319
  -2.500   0.3277   0.01333   0.00658  -0.1393   0.7479   0.6457
  -2.250   0.3534   0.01362   0.00685  -0.1385   0.7444   0.6590
  -2.000   0.3803   0.01385   0.00703  -0.1380   0.7413   0.6691
  -1.750   0.4104   0.01393   0.00699  -0.1386   0.7385   0.6767
  -1.500   0.4349   0.01399   0.00702  -0.1381   0.7342   0.6808
  -1.250   0.4610   0.01404   0.00703  -0.1379   0.7303   0.6835
  -1.000   0.4894   0.01405   0.00698  -0.1382   0.7269   0.6864
  -0.750   0.5197   0.01406   0.00689  -0.1389   0.7241   0.6895
  -0.500   0.5472   0.01408   0.00687  -0.1391   0.7203   0.6929
  -0.250   0.5741   0.01411   0.00684  -0.1394   0.7160   0.6960
   0.000   0.6009   0.01414   0.00685  -0.1393   0.7122   0.6979
   0.250   0.6297   0.01415   0.00683  -0.1396   0.7089   0.7001
   0.500   0.6579   0.01419   0.00684  -0.1399   0.7054   0.7024
   0.750   0.6821   0.01426   0.00692  -0.1395   0.7006   0.7049
   1.000   0.7096   0.01429   0.00693  -0.1397   0.6964   0.7078
   1.250   0.7399   0.01430   0.00688  -0.1405   0.6928   0.7110
   1.500   0.7668   0.01435   0.00692  -0.1406   0.6885   0.7133
   1.750   0.7903   0.01443   0.00704  -0.1399   0.6834   0.7152
   2.000   0.8173   0.01446   0.00708  -0.1399   0.6789   0.7172
   2.250   0.8475   0.01447   0.00705  -0.1406   0.6752   0.7196
   2.500   0.8689   0.01458   0.00723  -0.1396   0.6691   0.7226
   2.750   0.8952   0.01463   0.00728  -0.1396   0.6638   0.7255
   3.000   0.9260   0.01463   0.00725  -0.1404   0.6595   0.7283
   3.250   0.9465   0.01475   0.00744  -0.1392   0.6529   0.7304
   3.500   0.9715   0.01480   0.00752  -0.1388   0.6472   0.7325
   3.750   0.9981   0.01485   0.00760  -0.1388   0.6420   0.7349
   4.000   1.0192   0.01497   0.00779  -0.1377   0.6349   0.7379
   4.250   1.0464   0.01500   0.00782  -0.1378   0.6290   0.7409
   4.500   1.0678   0.01513   0.00802  -0.1369   0.6213   0.7440
   4.750   1.0926   0.01519   0.00809  -0.1365   0.6141   0.7464
   5.000   1.1127   0.01531   0.00829  -0.1352   0.6059   0.7487
   5.250   1.1358   0.01539   0.00840  -0.1345   0.5981   0.7514
   5.500   1.1548   0.01555   0.00863  -0.1330   0.5893   0.7547
   5.750   1.1777   0.01566   0.00873  -0.1322   0.5809   0.7581
   6.000   1.1936   0.01584   0.00899  -0.1302   0.5706   0.7617
   6.250   1.2107   0.01601   0.00921  -0.1284   0.5605   0.7643
   6.500   1.2288   0.01620   0.00941  -0.1267   0.5495   0.7672
   6.750   1.2437   0.01648   0.00975  -0.1246   0.5370   0.7707
   7.000   1.2595   0.01679   0.01009  -0.1227   0.5239   0.7746
   7.250   1.2745   0.01714   0.01046  -0.1207   0.5101   0.7785
   7.500   1.2879   0.01752   0.01087  -0.1184   0.4958   0.7820
   7.750   1.3002   0.01798   0.01134  -0.1160   0.4803   0.7861
   8.000   1.3116   0.01851   0.01187  -0.1136   0.4639   0.7904
   8.250   1.3219   0.01913   0.01248  -0.1111   0.4468   0.7947
   8.500   1.3303   0.01982   0.01317  -0.1083   0.4294   0.7987
   8.750   1.3379   0.02062   0.01395  -0.1056   0.4117   0.8037
   9.000   1.3453   0.02152   0.01483  -0.1030   0.3943   0.8094
   9.250   1.3501   0.02251   0.01582  -0.1001   0.3765   0.8145
   9.500   1.3557   0.02358   0.01688  -0.0975   0.3589   0.8204
   9.750   1.3612   0.02473   0.01803  -0.0951   0.3414   0.8266
  10.000   1.3651   0.02598   0.01927  -0.0925   0.3236   0.8329
  10.250   1.3692   0.02733   0.02062  -0.0901   0.3061   0.8404
  10.500   1.3728   0.02870   0.02201  -0.0878   0.2897   0.8485
  10.750   1.3761   0.03018   0.02350  -0.0855   0.2731   0.8586
  11.000   1.3787   0.03171   0.02503  -0.0833   0.2570   0.8712
  11.500   1.3797   0.03470   0.02812  -0.0782   0.2274   0.9300
  11.750   1.3818   0.03642   0.02984  -0.0765   0.2125   1.0000
  12.000   1.3861   0.03838   0.03177  -0.0753   0.1973   1.0000
  12.250   1.3900   0.04043   0.03380  -0.0742   0.1823   1.0000
  12.500   1.3937   0.04254   0.03589  -0.0731   0.1680   1.0000
  12.750   1.3971   0.04475   0.03808  -0.0722   0.1544   1.0000
  13.000   1.4004   0.04703   0.04036  -0.0713   0.1416   1.0000
  13.250   1.4035   0.04937   0.04270  -0.0705   0.1297   1.0000
  13.500   1.4059   0.05185   0.04518  -0.0698   0.1185   1.0000
  13.750   1.4084   0.05438   0.04771  -0.0692   0.1078   1.0000
  14.000   1.4116   0.05689   0.05025  -0.0687   0.0976   1.0000
  14.250   1.4137   0.05960   0.05298  -0.0682   0.0882   1.0000
  14.500   1.4149   0.06247   0.05587  -0.0679   0.0795   1.0000
  15.000   1.4167   0.06845   0.06192  -0.0676   0.0636   1.0000
  15.250   1.4170   0.07163   0.06515  -0.0675   0.0570   1.0000
  15.500   1.4157   0.07508   0.06863  -0.0677   0.0512   1.0000
  15.750   1.4161   0.07837   0.07199  -0.0679   0.0458   1.0000
  16.000   1.4150   0.08192   0.07562  -0.0682   0.0415   1.0000
  16.250   1.4131   0.08565   0.07941  -0.0687   0.0374   1.0000
  16.500   1.4118   0.08939   0.08325  -0.0693   0.0340   1.0000
  16.750   1.4089   0.09342   0.08735  -0.0702   0.0310   1.0000
  17.000   1.4069   0.09736   0.09141  -0.0710   0.0284   1.0000
  17.250   1.4036   0.10156   0.09570  -0.0721   0.0260   1.0000
  17.500   1.4001   0.10585   0.10009  -0.0734   0.0240   1.0000
  17.750   1.3969   0.11015   0.10452  -0.0748   0.0222   1.0000
  18.250   1.3885   0.11924   0.11382  -0.0781   0.0191   1.0000
  18.500   1.3839   0.12390   0.11859  -0.0800   0.0178   1.0000
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