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EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 393 AIRFOIL (e393-il)
Reynolds number: 100,000
Max Cl/Cd: 60.63 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e393-il-100000.txt
Download as CSV file: xf-e393-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3104   0.10674   0.10201  -0.0425   1.0000   0.0909
  -9.000  -0.3276   0.10530   0.10071  -0.0447   1.0000   0.0930
  -8.750  -0.3509   0.10420   0.09978  -0.0461   1.0000   0.0936
  -8.500  -0.3244   0.09863   0.09418  -0.0422   1.0000   0.0965
  -8.250  -0.3200   0.09649   0.09209  -0.0400   1.0000   0.1015
  -8.000  -0.3312   0.09476   0.09048  -0.0387   1.0000   0.1038
  -7.750  -0.3489   0.09356   0.08942  -0.0365   1.0000   0.1049
  -7.500  -0.3805   0.09354   0.08957  -0.0329   1.0000   0.1061
  -7.250  -0.4071   0.09333   0.08950  -0.0287   1.0000   0.1062
  -7.000  -0.4342   0.09284   0.08914  -0.0264   1.0000   0.1065
  -6.750  -0.4121   0.08799   0.08430  -0.0293   0.9948   0.1118
  -6.500  -0.3898   0.07878   0.07499  -0.0542   0.9795   0.1226
  -6.250  -0.3639   0.07795   0.07421  -0.0452   0.9765   0.1290
  -6.000  -0.3407   0.07138   0.06759  -0.0572   0.9660   0.1398
  -5.750  -0.3130   0.06547   0.06156  -0.0675   0.9574   0.1531
  -5.500  -0.2908   0.06085   0.05680  -0.0736   0.9472   0.1670
  -5.250  -0.2402   0.04017   0.03438  -0.0943   0.9406   0.0707
  -5.000  -0.2029   0.03499   0.02836  -0.0978   0.9336   0.0628
  -4.750  -0.1578   0.03095   0.02358  -0.1018   0.9298   0.0614
  -4.500  -0.1252   0.02911   0.02112  -0.1029   0.9213   0.0657
  -4.250  -0.0830   0.02645   0.01821  -0.1059   0.9172   0.0716
  -4.000  -0.0490   0.02524   0.01666  -0.1068   0.9096   0.0801
  -3.750  -0.0095   0.02344   0.01487  -0.1089   0.9045   0.0947
  -3.500   0.0354   0.02180   0.01341  -0.1122   0.9014   0.1250
  -3.250   0.0624   0.02060   0.01258  -0.1125   0.8924   0.1854
  -3.000   0.1044   0.01877   0.01211  -0.1158   0.8888   0.4623
  -2.750   0.1299   0.01889   0.01238  -0.1148   0.8802   0.5641
  -2.500   0.1650   0.01884   0.01230  -0.1152   0.8750   0.6284
  -2.250   0.1886   0.01898   0.01241  -0.1138   0.8667   0.6714
  -2.000   0.2191   0.01888   0.01230  -0.1132   0.8611   0.7109
  -1.750   0.2408   0.01898   0.01237  -0.1114   0.8530   0.7445
  -1.500   0.2676   0.01885   0.01222  -0.1102   0.8471   0.7769
  -1.250   0.2859   0.01894   0.01228  -0.1078   0.8390   0.8072
  -1.000   0.3094   0.01879   0.01210  -0.1060   0.8329   0.8395
  -0.750   0.3246   0.01885   0.01215  -0.1031   0.8248   0.8733
  -0.500   0.3467   0.01862   0.01189  -0.1011   0.8188   0.9134
  -0.250   0.3935   0.01833   0.01152  -0.1044   0.8139   0.9640
   0.000   0.4389   0.01837   0.01142  -0.1093   0.8065   1.0000
   0.250   0.4814   0.01826   0.01113  -0.1127   0.8022   1.0000
   0.500   0.5067   0.01878   0.01152  -0.1137   0.7928   1.0000
   0.750   0.5455   0.01875   0.01134  -0.1158   0.7883   1.0000
   1.000   0.5685   0.01934   0.01186  -0.1159   0.7793   1.0000
   1.250   0.6043   0.01936   0.01177  -0.1173   0.7745   1.0000
   1.500   0.6263   0.01998   0.01234  -0.1170   0.7657   1.0000
   1.750   0.6602   0.02005   0.01235  -0.1180   0.7607   1.0000
   2.000   0.6821   0.02069   0.01297  -0.1175   0.7522   1.0000
   2.250   0.7146   0.02080   0.01304  -0.1183   0.7469   1.0000
   2.500   0.7366   0.02144   0.01368  -0.1178   0.7386   1.0000
   2.750   0.7680   0.02159   0.01382  -0.1183   0.7329   1.0000
   3.000   0.7901   0.02222   0.01448  -0.1178   0.7247   1.0000
   3.250   0.8212   0.02236   0.01461  -0.1181   0.7187   1.0000
   3.500   0.8430   0.02300   0.01529  -0.1175   0.7103   1.0000
   3.750   0.8749   0.02304   0.01537  -0.1179   0.7042   1.0000
   4.000   0.8960   0.02367   0.01607  -0.1170   0.6950   1.0000
   4.250   0.9304   0.02352   0.01593  -0.1175   0.6890   1.0000
   4.500   0.9501   0.02418   0.01668  -0.1165   0.6790   1.0000
   4.750   0.9876   0.02380   0.01635  -0.1172   0.6734   1.0000
   5.000   1.0071   0.02439   0.01705  -0.1161   0.6625   1.0000
   5.250   1.0316   0.02466   0.01741  -0.1153   0.6525   1.0000
   5.500   1.0688   0.02412   0.01690  -0.1158   0.6451   1.0000
   5.750   1.0908   0.02441   0.01734  -0.1146   0.6333   1.0000
   6.000   1.1159   0.02446   0.01751  -0.1138   0.6217   1.0000
   6.250   1.1438   0.02427   0.01741  -0.1131   0.6100   1.0000
   6.500   1.1729   0.02395   0.01719  -0.1124   0.5977   1.0000
   6.750   1.2010   0.02363   0.01695  -0.1117   0.5844   1.0000
   7.000   1.2268   0.02333   0.01681  -0.1105   0.5692   1.0000
   7.250   1.2516   0.02301   0.01660  -0.1092   0.5524   1.0000
   7.500   1.2773   0.02257   0.01626  -0.1080   0.5341   1.0000
   7.750   1.2992   0.02230   0.01609  -0.1062   0.5132   1.0000
   8.000   1.3202   0.02199   0.01584  -0.1042   0.4885   1.0000
   8.250   1.3343   0.02201   0.01602  -0.1014   0.4577   1.0000
   8.500   1.3460   0.02220   0.01622  -0.0983   0.4193   1.0000
   8.750   1.3516   0.02280   0.01671  -0.0945   0.3708   1.0000
   9.000   1.3506   0.02395   0.01754  -0.0899   0.3167   1.0000
   9.250   1.3432   0.02554   0.01878  -0.0849   0.2695   1.0000
   9.500   1.3344   0.02745   0.02040  -0.0801   0.2301   1.0000
   9.750   1.3260   0.02960   0.02228  -0.0759   0.1971   1.0000
  10.000   1.3184   0.03193   0.02439  -0.0724   0.1690   1.0000
  10.250   1.3122   0.03439   0.02669  -0.0694   0.1435   1.0000
  10.500   1.3065   0.03700   0.02917  -0.0669   0.1210   1.0000
  10.750   1.3004   0.03981   0.03182  -0.0648   0.1020   1.0000
  11.000   1.2960   0.04274   0.03470  -0.0630   0.0837   1.0000
  11.250   1.2923   0.04580   0.03771  -0.0613   0.0689   1.0000
  11.500   1.2916   0.04885   0.04072  -0.0597   0.0575   1.0000
  11.750   1.2952   0.05171   0.04359  -0.0583   0.0493   1.0000
  12.000   1.3026   0.05421   0.04612  -0.0571   0.0437   1.0000
  12.250   1.3263   0.05675   0.04872  -0.0555   0.0395   1.0000
  12.500   1.3446   0.05949   0.05173  -0.0542   0.0370   1.0000
  12.750   1.3586   0.06263   0.05513  -0.0532   0.0355   1.0000
  13.000   1.3659   0.06604   0.05878  -0.0523   0.0344   1.0000
  13.250   1.3703   0.06963   0.06255  -0.0517   0.0333   1.0000
  13.500   1.3739   0.07439   0.06749  -0.0512   0.0322   1.0000
  13.750   1.3648   0.08007   0.07346  -0.0509   0.0317   1.0000
  14.000   1.3497   0.08463   0.07833  -0.0510   0.0316   1.0000
  14.250   1.3338   0.08967   0.08366  -0.0516   0.0315   1.0000
  14.500   1.3167   0.09512   0.08939  -0.0528   0.0315   1.0000
  14.750   1.2992   0.10101   0.09554  -0.0544   0.0316   1.0000
  15.000   1.2815   0.10730   0.10206  -0.0567   0.0317   1.0000
  15.250   1.2637   0.11359   0.10861  -0.0596   0.0318   1.0000
  15.500   1.2449   0.12002   0.11527  -0.0633   0.0320   1.0000
  15.750   0.9789   0.13589   0.13235  -0.0703   0.0402   1.0000
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