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EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 393 AIRFOIL (e393-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.45 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e393-il-1000000-n5.txt
Download as CSV file: xf-e393-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 393 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3571   0.11540   0.11373  -0.0381   1.0000   0.0040
 -11.250  -0.3520   0.11090   0.10923  -0.0407   0.9995   0.0038
 -10.750  -0.5709   0.04168   0.03986  -0.0890   0.9849   0.0040
 -10.250  -0.5625   0.02541   0.02265  -0.1133   0.9597   0.0040
 -10.000  -0.5403   0.02272   0.01964  -0.1160   0.9482   0.0040
  -9.750  -0.5154   0.02049   0.01709  -0.1181   0.9324   0.0041
  -9.500  -0.4917   0.01878   0.01507  -0.1190   0.9109   0.0042
  -9.250  -0.4692   0.01769   0.01372  -0.1191   0.8877   0.0042
  -9.000  -0.4465   0.01691   0.01272  -0.1188   0.8665   0.0043
  -8.750  -0.4236   0.01615   0.01176  -0.1185   0.8472   0.0044
  -8.500  -0.3998   0.01553   0.01095  -0.1182   0.8295   0.0045
  -8.250  -0.3755   0.01492   0.01017  -0.1180   0.8134   0.0045
  -8.000  -0.3528   0.01368   0.00866  -0.1179   0.7988   0.0047
  -7.750  -0.3284   0.01280   0.00757  -0.1177   0.7852   0.0049
  -7.500  -0.3029   0.01219   0.00680  -0.1177   0.7723   0.0052
  -7.250  -0.2765   0.01175   0.00626  -0.1176   0.7605   0.0054
  -7.000  -0.2498   0.01139   0.00580  -0.1177   0.7496   0.0057
  -6.750  -0.2229   0.01104   0.00534  -0.1177   0.7394   0.0060
  -6.500  -0.1959   0.01072   0.00492  -0.1177   0.7295   0.0063
  -6.250  -0.1685   0.01041   0.00452  -0.1177   0.7202   0.0066
  -6.000  -0.1409   0.01015   0.00416  -0.1178   0.7117   0.0069
  -5.750  -0.1134   0.00990   0.00383  -0.1179   0.7031   0.0071
  -5.500  -0.0855   0.00961   0.00346  -0.1180   0.6954   0.0076
  -5.000  -0.0296   0.00917   0.00291  -0.1182   0.6808   0.0097
  -4.500   0.0267   0.00882   0.00250  -0.1185   0.6674   0.0144
  -4.250   0.0548   0.00869   0.00231  -0.1186   0.6609   0.0170
  -4.000   0.0832   0.00854   0.00215  -0.1188   0.6552   0.0202
  -3.750   0.1116   0.00842   0.00199  -0.1189   0.6491   0.0231
  -3.500   0.1398   0.00830   0.00185  -0.1191   0.6435   0.0292
  -3.250   0.1684   0.00813   0.00172  -0.1193   0.6381   0.0429
  -3.000   0.1967   0.00796   0.00160  -0.1196   0.6327   0.0640
  -2.750   0.2252   0.00780   0.00149  -0.1198   0.6277   0.0880
  -2.500   0.2538   0.00767   0.00140  -0.1200   0.6222   0.1108
  -2.250   0.2822   0.00755   0.00132  -0.1202   0.6173   0.1383
  -1.750   0.3395   0.00716   0.00119  -0.1209   0.6075   0.2398
  -1.500   0.3680   0.00692   0.00114  -0.1213   0.6025   0.3160
  -1.250   0.3967   0.00678   0.00112  -0.1216   0.5981   0.3640
  -1.000   0.4253   0.00670   0.00111  -0.1218   0.5931   0.4008
  -0.500   0.4823   0.00660   0.00113  -0.1222   0.5836   0.4694
  -0.250   0.5108   0.00659   0.00115  -0.1224   0.5785   0.4906
   0.250   0.5676   0.00659   0.00120  -0.1227   0.5689   0.5294
   0.500   0.5960   0.00660   0.00123  -0.1228   0.5637   0.5455
   0.750   0.6241   0.00663   0.00127  -0.1229   0.5587   0.5619
   1.000   0.6526   0.00664   0.00131  -0.1231   0.5536   0.5790
   1.250   0.6807   0.00667   0.00136  -0.1231   0.5479   0.5954
   1.500   0.7089   0.00670   0.00142  -0.1232   0.5421   0.6121
   2.000   0.7647   0.00679   0.00154  -0.1234   0.5264   0.6428
   2.250   0.7925   0.00685   0.00162  -0.1234   0.5185   0.6579
   2.500   0.8203   0.00689   0.00170  -0.1235   0.5107   0.6736
   2.750   0.8477   0.00697   0.00179  -0.1234   0.5011   0.6909
   3.000   0.8753   0.00704   0.00188  -0.1234   0.4914   0.7098
   3.250   0.9027   0.00710   0.00200  -0.1234   0.4826   0.7303
   3.500   0.9297   0.00719   0.00211  -0.1233   0.4710   0.7529
   3.750   0.9562   0.00729   0.00224  -0.1231   0.4572   0.7779
   4.000   0.9825   0.00740   0.00238  -0.1229   0.4444   0.8059
   4.250   1.0081   0.00750   0.00255  -0.1225   0.4301   0.8384
   4.500   1.0321   0.00762   0.00271  -0.1217   0.4127   0.8773
   4.750   1.0514   0.00778   0.00288  -0.1199   0.3884   0.9333
   5.000   1.0764   0.00803   0.00306  -0.1195   0.3621   1.0000
   5.250   1.1003   0.00845   0.00333  -0.1190   0.3289   1.0000
   5.500   1.1234   0.00893   0.00366  -0.1184   0.2937   1.0000
   5.750   1.1443   0.00959   0.00408  -0.1174   0.2477   1.0000
   6.000   1.1635   0.01038   0.00457  -0.1162   0.1948   1.0000
   6.250   1.1828   0.01112   0.00506  -0.1150   0.1498   1.0000
   6.500   1.2046   0.01164   0.00546  -0.1141   0.1253   1.0000
   6.750   1.2267   0.01211   0.00585  -0.1134   0.1063   1.0000
   7.000   1.2468   0.01271   0.00632  -0.1123   0.0820   1.0000
   7.250   1.2665   0.01331   0.00680  -0.1111   0.0616   1.0000
   7.500   1.2856   0.01393   0.00731  -0.1098   0.0437   1.0000
   7.750   1.3044   0.01453   0.00783  -0.1085   0.0301   1.0000
   8.000   1.3232   0.01510   0.00837  -0.1072   0.0205   1.0000
   8.250   1.3413   0.01569   0.00892  -0.1058   0.0134   1.0000
   8.500   1.3573   0.01636   0.00955  -0.1040   0.0070   1.0000
   8.750   1.3728   0.01691   0.01011  -0.1020   0.0048   1.0000
   9.000   1.3879   0.01743   0.01066  -0.1000   0.0040   1.0000
   9.250   1.4021   0.01799   0.01126  -0.0979   0.0036   1.0000
   9.500   1.4154   0.01861   0.01193  -0.0958   0.0031   1.0000
   9.750   1.4286   0.01926   0.01263  -0.0936   0.0030   1.0000
  10.000   1.4418   0.01992   0.01336  -0.0916   0.0029   1.0000
  10.250   1.4543   0.02065   0.01414  -0.0896   0.0028   1.0000
  10.500   1.4659   0.02145   0.01501  -0.0876   0.0026   1.0000
  10.750   1.4767   0.02234   0.01596  -0.0856   0.0025   1.0000
  11.000   1.4868   0.02332   0.01701  -0.0836   0.0025   1.0000
  11.250   1.4961   0.02440   0.01815  -0.0817   0.0024   1.0000
  11.500   1.5048   0.02557   0.01940  -0.0799   0.0023   1.0000
  11.750   1.5134   0.02681   0.02070  -0.0782   0.0022   1.0000
  12.000   1.5212   0.02818   0.02214  -0.0766   0.0021   1.0000
  12.250   1.5285   0.02963   0.02369  -0.0751   0.0020   1.0000
  12.500   1.5345   0.03128   0.02541  -0.0737   0.0020   1.0000
  12.750   1.5401   0.03304   0.02725  -0.0724   0.0019   1.0000
  13.000   1.5443   0.03499   0.02929  -0.0711   0.0019   1.0000
  13.250   1.5476   0.03712   0.03151  -0.0700   0.0018   1.0000
  13.500   1.5498   0.03943   0.03392  -0.0690   0.0018   1.0000
  13.750   1.5503   0.04201   0.03660  -0.0682   0.0017   1.0000
  14.000   1.5503   0.04475   0.03945  -0.0675   0.0017   1.0000
  14.250   1.5473   0.04791   0.04274  -0.0669   0.0016   1.0000
  14.500   1.5462   0.05098   0.04591  -0.0666   0.0016   1.0000
  14.750   1.5395   0.05486   0.04994  -0.0665   0.0016   1.0000
  15.000   1.5340   0.05875   0.05395  -0.0666   0.0016   1.0000
  15.250   1.5324   0.06225   0.05756  -0.0668   0.0016   1.0000
  15.500   1.5321   0.06568   0.06109  -0.0673   0.0015   1.0000
  15.750   1.5281   0.06976   0.06530  -0.0680   0.0015   1.0000
  16.000   1.5262   0.07362   0.06926  -0.0688   0.0015   1.0000
  16.250   1.5200   0.07829   0.07406  -0.0699   0.0015   1.0000
  16.500   1.5165   0.08267   0.07856  -0.0711   0.0015   1.0000
  16.750   1.5104   0.08756   0.08357  -0.0726   0.0015   1.0000
  17.000   1.5048   0.09252   0.08864  -0.0743   0.0015   1.0000
  17.250   1.4973   0.09796   0.09421  -0.0764   0.0015   1.0000
  17.500   1.4886   0.10372   0.10010  -0.0787   0.0015   1.0000
  17.750   1.4807   0.10946   0.10595  -0.0811   0.0015   1.0000
  18.000   1.4706   0.11575   0.11238  -0.0840   0.0015   1.0000
  18.250   1.4611   0.12205   0.11880  -0.0870   0.0015   1.0000
  18.500   1.4510   0.12860   0.12549  -0.0904   0.0015   1.0000
  18.750   1.4402   0.13540   0.13241  -0.0940   0.0015   1.0000
  19.000   1.4301   0.14218   0.13931  -0.0978   0.0014   1.0000
  19.250   1.4194   0.14919   0.14644  -0.1019   0.0014   1.0000
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