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E392 (10.15%) (e392-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E392 (10.15%) (e392-il)
Reynolds number: 200,000
Max Cl/Cd: 86.19 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e392-il-200000.txt
Download as CSV file: xf-e392-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E392  (10.15%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3185   0.08934   0.08604  -0.0397   1.0000   0.0418
  -8.000  -0.3185   0.08676   0.08353  -0.0396   1.0000   0.0429
  -7.750  -0.3218   0.08437   0.08121  -0.0392   1.0000   0.0437
  -7.500  -0.3309   0.08233   0.07927  -0.0379   1.0000   0.0444
  -7.250  -0.3527   0.08159   0.07866  -0.0338   1.0000   0.0446
  -7.000  -0.3403   0.07678   0.07389  -0.0420   0.9923   0.0471
  -6.750  -0.2924   0.06468   0.06143  -0.0743   0.9752   0.0498
  -6.500  -0.2735   0.05849   0.05539  -0.0762   0.9714   0.0516
  -6.250  -0.2469   0.05530   0.05219  -0.0792   0.9624   0.0537
  -6.000  -0.2115   0.04960   0.04628  -0.0883   0.9542   0.0590
  -5.750  -0.1789   0.04231   0.03852  -0.0978   0.9437   0.0646
  -5.500  -0.1510   0.04019   0.03639  -0.0994   0.9325   0.0709
  -5.250  -0.1227   0.03605   0.03189  -0.1032   0.9204   0.0796
  -5.000  -0.0880   0.02540   0.01972  -0.1050   0.9092   0.0373
  -4.750  -0.0592   0.02168   0.01548  -0.1057   0.8990   0.0344
  -4.500  -0.0314   0.01918   0.01245  -0.1053   0.8869   0.0328
  -4.250  -0.0040   0.01753   0.01048  -0.1048   0.8747   0.0329
  -4.000   0.0231   0.01630   0.00904  -0.1043   0.8633   0.0343
  -3.750   0.0503   0.01541   0.00798  -0.1038   0.8528   0.0371
  -3.500   0.0764   0.01438   0.00687  -0.1033   0.8424   0.0427
  -3.250   0.1030   0.01368   0.00607  -0.1028   0.8315   0.0502
  -3.000   0.1295   0.01261   0.00513  -0.1026   0.8219   0.0915
  -2.750   0.1560   0.01183   0.00470  -0.1026   0.8130   0.1824
  -2.500   0.1812   0.01104   0.00453  -0.1027   0.8032   0.3532
  -2.250   0.2065   0.01060   0.00450  -0.1023   0.7952   0.5009
  -2.000   0.2315   0.01037   0.00449  -0.1015   0.7863   0.5976
  -1.750   0.2559   0.01022   0.00449  -0.1004   0.7784   0.6751
  -1.500   0.2791   0.01009   0.00447  -0.0989   0.7707   0.7459
  -1.250   0.3004   0.00998   0.00447  -0.0969   0.7630   0.8130
  -1.000   0.3206   0.00987   0.00441  -0.0945   0.7559   0.8832
  -0.750   0.3589   0.00973   0.00422  -0.0961   0.7488   0.9720
  -0.500   0.3930   0.00979   0.00410  -0.0976   0.7416   1.0000
  -0.250   0.4207   0.00992   0.00409  -0.0978   0.7346   1.0000
   0.000   0.4486   0.01005   0.00408  -0.0979   0.7277   1.0000
   0.250   0.4764   0.01020   0.00411  -0.0980   0.7213   1.0000
   0.500   0.5040   0.01034   0.00416  -0.0980   0.7142   1.0000
   0.750   0.5321   0.01050   0.00420  -0.0981   0.7085   1.0000
   1.000   0.5594   0.01065   0.00431  -0.0981   0.7012   1.0000
   1.250   0.5876   0.01081   0.00435  -0.0981   0.6957   1.0000
   1.500   0.6147   0.01098   0.00451  -0.0981   0.6886   1.0000
   1.750   0.6426   0.01114   0.00461  -0.0981   0.6827   1.0000
   2.000   0.6700   0.01132   0.00477  -0.0981   0.6763   1.0000
   2.250   0.6975   0.01149   0.00491  -0.0981   0.6698   1.0000
   2.500   0.7253   0.01168   0.00505  -0.0981   0.6640   1.0000
   2.750   0.7522   0.01185   0.00526  -0.0980   0.6568   1.0000
   3.000   0.7805   0.01202   0.00536  -0.0980   0.6513   1.0000
   3.250   0.8067   0.01220   0.00560  -0.0978   0.6431   1.0000
   3.500   0.8348   0.01234   0.00568  -0.0977   0.6369   1.0000
   3.750   0.8608   0.01249   0.00593  -0.0974   0.6280   1.0000
   4.000   0.8883   0.01263   0.00604  -0.0973   0.6209   1.0000
   4.250   0.9146   0.01276   0.00623  -0.0970   0.6119   1.0000
   4.500   0.9413   0.01289   0.00641  -0.0967   0.6034   1.0000
   4.750   0.9683   0.01298   0.00650  -0.0964   0.5946   1.0000
   5.000   0.9940   0.01309   0.00670  -0.0960   0.5843   1.0000
   5.250   1.0203   0.01319   0.00684  -0.0956   0.5745   1.0000
   5.500   1.0469   0.01326   0.00693  -0.0952   0.5644   1.0000
   5.750   1.0720   0.01334   0.00711  -0.0946   0.5521   1.0000
   6.000   1.0970   0.01340   0.00726  -0.0940   0.5388   1.0000
   6.250   1.1217   0.01346   0.00740  -0.0933   0.5239   1.0000
   6.500   1.1457   0.01353   0.00750  -0.0925   0.5058   1.0000
   6.750   1.1681   0.01360   0.00762  -0.0913   0.4800   1.0000
   7.000   1.1894   0.01380   0.00780  -0.0901   0.4486   1.0000
   7.250   1.2091   0.01416   0.00811  -0.0887   0.4079   1.0000
   7.500   1.2247   0.01486   0.00856  -0.0867   0.3471   1.0000
   7.750   1.2349   0.01605   0.00935  -0.0842   0.2744   1.0000
   8.000   1.2433   0.01747   0.01039  -0.0817   0.2109   1.0000
   8.250   1.2518   0.01888   0.01150  -0.0792   0.1574   1.0000
   8.500   1.2564   0.02054   0.01281  -0.0763   0.1036   1.0000
   8.750   1.2513   0.02274   0.01460  -0.0720   0.0560   1.0000
   9.000   1.2483   0.02457   0.01635  -0.0678   0.0431   1.0000
   9.250   1.2515   0.02606   0.01796  -0.0648   0.0383   1.0000
   9.500   1.2554   0.02759   0.01954  -0.0622   0.0348   1.0000
   9.750   1.2516   0.02981   0.02181  -0.0593   0.0326   1.0000
  10.000   1.2579   0.03145   0.02357  -0.0574   0.0311   1.0000
  10.250   1.2635   0.03326   0.02549  -0.0556   0.0298   1.0000
  10.500   1.2700   0.03514   0.02746  -0.0539   0.0285   1.0000
  10.750   1.2777   0.03704   0.02944  -0.0524   0.0276   1.0000
  11.000   1.2870   0.03897   0.03143  -0.0510   0.0266   1.0000
  11.250   1.2991   0.04094   0.03345  -0.0497   0.0258   1.0000
  11.500   1.3243   0.04390   0.03648  -0.0486   0.0243   1.0000
  11.750   1.3326   0.04572   0.03852  -0.0474   0.0237   1.0000
  12.000   1.3440   0.04802   0.04106  -0.0463   0.0232   1.0000
  12.250   1.3543   0.05078   0.04409  -0.0451   0.0229   1.0000
  12.500   1.3606   0.05395   0.04754  -0.0440   0.0228   1.0000
  12.750   1.3615   0.05751   0.05140  -0.0429   0.0227   1.0000
  13.000   1.3578   0.06144   0.05562  -0.0419   0.0227   1.0000
  13.250   1.3499   0.06574   0.06022  -0.0413   0.0228   1.0000
  13.500   1.3384   0.07043   0.06519  -0.0411   0.0229   1.0000
  13.750   1.3244   0.07540   0.07043  -0.0414   0.0230   1.0000
  14.000   1.3081   0.08079   0.07607  -0.0423   0.0231   1.0000
  14.250   1.2904   0.08653   0.08205  -0.0437   0.0232   1.0000
  14.500   1.2714   0.09274   0.08848  -0.0458   0.0233   1.0000
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