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EPPLER 336 AIRFOIL (e336-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 336 AIRFOIL (e336-il)
Reynolds number: 500,000
Max Cl/Cd: 78.63 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e336-il-500000-n5.txt
Download as CSV file: xf-e336-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 336 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3445   0.09883   0.09626  -0.0129   0.7771   0.0110
 -10.250  -0.3458   0.09449   0.09183  -0.0145   0.7542   0.0110
  -9.750  -0.4518   0.08754   0.08539  -0.0192   1.0000   0.0105
  -7.500  -0.5202   0.04826   0.04434  -0.0209   0.6561   0.0082
  -7.000  -0.5278   0.03637   0.03171  -0.0120   0.6370   0.0057
  -6.750  -0.5208   0.03326   0.02830  -0.0089   0.6251   0.0056
  -6.500  -0.5137   0.02949   0.02413  -0.0055   0.6145   0.0055
  -6.250  -0.5018   0.02633   0.02055  -0.0026   0.6038   0.0053
  -6.000  -0.4866   0.02327   0.01703   0.0000   0.5932   0.0052
  -5.750  -0.4663   0.02119   0.01455   0.0017   0.5823   0.0051
  -5.500  -0.4434   0.01937   0.01237   0.0029   0.5710   0.0051
  -5.250  -0.4188   0.01802   0.01074   0.0037   0.5597   0.0051
  -5.000  -0.3933   0.01689   0.00938   0.0044   0.5497   0.0051
  -4.750  -0.3680   0.01600   0.00830   0.0051   0.5402   0.0052
  -4.500  -0.3429   0.01525   0.00741   0.0058   0.5311   0.0052
  -4.250  -0.3183   0.01467   0.00672   0.0065   0.5225   0.0052
  -4.000  -0.2940   0.01411   0.00605   0.0073   0.5139   0.0054
  -3.750  -0.2699   0.01364   0.00550   0.0082   0.5059   0.0055
  -3.500  -0.2457   0.01325   0.00502   0.0090   0.4978   0.0057
  -3.250  -0.2219   0.01283   0.00454   0.0099   0.4903   0.0059
  -3.000  -0.1976   0.01251   0.00417   0.0107   0.4824   0.0063
  -2.750  -0.1730   0.01226   0.00385   0.0114   0.4752   0.0069
  -2.500  -0.1481   0.01204   0.00358   0.0121   0.4677   0.0077
  -2.250  -0.1236   0.01183   0.00330   0.0128   0.4607   0.0089
  -2.000  -0.0986   0.01163   0.00308   0.0135   0.4536   0.0115
  -1.750  -0.0740   0.01145   0.00288   0.0142   0.4465   0.0182
  -1.500  -0.0503   0.01117   0.00273   0.0150   0.4397   0.0477
  -1.250  -0.0273   0.01087   0.00260   0.0159   0.4322   0.1003
  -1.000  -0.0091   0.01022   0.00244   0.0176   0.4259   0.2427
  -0.750  -0.0249   0.00795   0.00255   0.0267   0.4218   0.8357
  -0.250   0.0201   0.00859   0.00308   0.0301   0.4091   0.8971
   0.000   0.0545   0.00904   0.00345   0.0293   0.4009   0.9066
   0.250   0.0786   0.00931   0.00364   0.0305   0.3935   0.9160
   0.500   0.1274   0.00986   0.00408   0.0267   0.3834   0.9202
   0.750   0.1603   0.01001   0.00415   0.0257   0.3759   0.9225
   1.000   0.1854   0.01005   0.00411   0.0263   0.3696   0.9245
   1.250   0.2052   0.01004   0.00404   0.0280   0.3649   0.9275
   1.500   0.2211   0.00999   0.00395   0.0304   0.3603   0.9309
   1.750   0.2499   0.01004   0.00393   0.0301   0.3555   0.9315
   2.000   0.2787   0.01011   0.00393   0.0299   0.3515   0.9322
   2.250   0.3073   0.01015   0.00395   0.0296   0.3482   0.9329
   2.500   0.3350   0.01020   0.00396   0.0296   0.3450   0.9336
   2.750   0.3628   0.01027   0.00399   0.0295   0.3418   0.9345
   3.000   0.3898   0.01036   0.00403   0.0296   0.3385   0.9354
   3.250   0.4163   0.01041   0.00406   0.0297   0.3361   0.9364
   3.500   0.4421   0.01045   0.00410   0.0300   0.3337   0.9374
   3.750   0.4677   0.01051   0.00415   0.0304   0.3311   0.9387
   4.000   0.4915   0.01056   0.00419   0.0311   0.3285   0.9402
   4.250   0.5135   0.01062   0.00423   0.0321   0.3256   0.9418
   4.500   0.5336   0.01069   0.00427   0.0336   0.3231   0.9436
   4.750   0.5530   0.01070   0.00430   0.0352   0.3211   0.9456
   5.000   0.5810   0.01076   0.00439   0.0350   0.3184   0.9462
   5.250   0.6083   0.01084   0.00448   0.0349   0.3156   0.9467
   5.500   0.6352   0.01094   0.00459   0.0349   0.3124   0.9473
   5.750   0.6615   0.01106   0.00471   0.0350   0.3092   0.9480
   6.000   0.6877   0.01119   0.00484   0.0350   0.3060   0.9487
   6.250   0.7147   0.01124   0.00496   0.0350   0.3030   0.9494
   6.500   0.7410   0.01133   0.00508   0.0351   0.2996   0.9502
   6.750   0.7666   0.01143   0.00521   0.0353   0.2956   0.9511
   7.000   0.7914   0.01157   0.00536   0.0356   0.2921   0.9522
   7.250   0.8173   0.01164   0.00549   0.0358   0.2881   0.9534
   7.500   0.8420   0.01172   0.00562   0.0362   0.2834   0.9547
   7.750   0.8651   0.01182   0.00575   0.0368   0.2776   0.9560
   8.000   0.8883   0.01189   0.00587   0.0375   0.2711   0.9574
   8.250   0.9096   0.01200   0.00599   0.0385   0.2643   0.9589
   8.500   0.9326   0.01212   0.00615   0.0391   0.2564   0.9601
   8.750   0.9579   0.01232   0.00636   0.0392   0.2481   0.9609
   9.000   0.9830   0.01255   0.00660   0.0393   0.2392   0.9617
   9.250   1.0073   0.01281   0.00689   0.0394   0.2304   0.9627
   9.500   1.0303   0.01313   0.00721   0.0398   0.2207   0.9639
   9.750   1.0530   0.01346   0.00755   0.0402   0.2095   0.9652
  10.000   1.0749   0.01381   0.00792   0.0407   0.1985   0.9668
  10.250   1.0944   0.01422   0.00832   0.0416   0.1860   0.9690
  10.500   1.1111   0.01465   0.00875   0.0430   0.1742   0.9714
  10.750   1.1280   0.01518   0.00926   0.0442   0.1601   0.9734
  11.000   1.1486   0.01581   0.00988   0.0444   0.1464   0.9748
  11.250   1.1675   0.01650   0.01056   0.0448   0.1332   0.9765
  11.500   1.1834   0.01725   0.01130   0.0457   0.1206   0.9790
  11.750   1.1962   0.01808   0.01212   0.0469   0.1087   0.9823
  12.000   1.2099   0.01904   0.01309   0.0475   0.0977   0.9850
  12.250   1.2264   0.02021   0.01427   0.0470   0.0871   0.9868
  12.500   1.2399   0.02159   0.01567   0.0464   0.0783   0.9892
  12.750   1.2510   0.02320   0.01732   0.0458   0.0699   0.9925
  13.000   1.2615   0.02505   0.01923   0.0446   0.0634   0.9966
  13.250   1.2698   0.02745   0.02167   0.0429   0.0568   1.0000
  13.500   1.2569   0.02946   0.02375   0.0457   0.0536   1.0000
  13.750   1.2479   0.03198   0.02630   0.0469   0.0502   1.0000
  14.000   1.2421   0.03459   0.02898   0.0474   0.0474   1.0000
  14.250   1.2339   0.03764   0.03209   0.0476   0.0437   1.0000
  14.750   1.2184   0.04404   0.03863   0.0473   0.0392   1.0000
  15.000   1.2083   0.04762   0.04226   0.0469   0.0362   1.0000
  15.250   1.1987   0.05123   0.04594   0.0464   0.0348   1.0000
  15.500   1.1902   0.05481   0.04960   0.0458   0.0334   1.0000
  15.750   1.1819   0.05851   0.05337   0.0450   0.0313   1.0000
  16.000   1.1742   0.06227   0.05721   0.0441   0.0299   1.0000
  16.250   1.1630   0.06656   0.06154   0.0429   0.0278   1.0000
  16.500   1.1573   0.07024   0.06531   0.0419   0.0269   1.0000
  16.750   1.1502   0.07423   0.06937   0.0407   0.0253   1.0000
  17.000   1.1409   0.07852   0.07372   0.0393   0.0235   1.0000
  17.250   1.1339   0.08260   0.07787   0.0379   0.0225   1.0000
  17.500   1.1288   0.08649   0.08185   0.0366   0.0217   1.0000
  17.750   1.1228   0.09053   0.08596   0.0351   0.0204   1.0000
  18.000   1.1149   0.09492   0.09040   0.0335   0.0192   1.0000
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