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EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 341 AIRFOIL (e341-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.72 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e341-il-1000000-n5.txt
Download as CSV file: xf-e341-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 341 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5621   0.07766   0.07497  -0.0137   0.6136   0.0049
  -9.500  -0.6043   0.06787   0.06507  -0.0173   0.6127   0.0048
  -9.000  -0.6586   0.05413   0.05095  -0.0129   0.6032   0.0047
  -8.500  -0.7239   0.02994   0.02546  -0.0004   0.6006   0.0045
  -8.250  -0.7119   0.02730   0.02247   0.0018   0.5905   0.0045
  -8.000  -0.6967   0.02522   0.02006   0.0036   0.5800   0.0046
  -7.750  -0.6809   0.02302   0.01751   0.0055   0.5692   0.0046
  -7.500  -0.6614   0.02145   0.01567   0.0068   0.5585   0.0046
  -7.250  -0.6395   0.02030   0.01431   0.0078   0.5477   0.0046
  -7.000  -0.6170   0.01915   0.01296   0.0087   0.5381   0.0046
  -6.750  -0.5935   0.01810   0.01172   0.0095   0.5294   0.0046
  -6.500  -0.5695   0.01712   0.01056   0.0102   0.5202   0.0046
  -6.250  -0.5449   0.01630   0.00959   0.0109   0.5121   0.0046
  -6.000  -0.5201   0.01550   0.00866   0.0115   0.5031   0.0046
  -5.750  -0.4951   0.01481   0.00784   0.0121   0.4945   0.0046
  -5.500  -0.4701   0.01421   0.00712   0.0126   0.4854   0.0046
  -5.250  -0.4452   0.01360   0.00643   0.0133   0.4779   0.0047
  -5.000  -0.4200   0.01314   0.00588   0.0138   0.4703   0.0047
  -4.750  -0.3948   0.01269   0.00537   0.0144   0.4638   0.0048
  -4.500  -0.3693   0.01233   0.00495   0.0149   0.4567   0.0049
  -4.250  -0.3436   0.01202   0.00458   0.0153   0.4495   0.0050
  -4.000  -0.3177   0.01174   0.00426   0.0158   0.4427   0.0051
  -3.750  -0.2917   0.01150   0.00397   0.0162   0.4355   0.0052
  -3.500  -0.2654   0.01128   0.00371   0.0166   0.4301   0.0054
  -3.250  -0.2392   0.01107   0.00347   0.0169   0.4241   0.0057
  -2.750  -0.1862   0.01074   0.00305   0.0176   0.4137   0.0064
  -2.500  -0.1597   0.01058   0.00286   0.0179   0.4079   0.0069
  -2.250  -0.1333   0.01044   0.00269   0.0183   0.4021   0.0080
  -2.000  -0.1065   0.01032   0.00255   0.0185   0.3974   0.0094
  -1.750  -0.0798   0.01020   0.00242   0.0188   0.3925   0.0120
  -1.500  -0.0535   0.01007   0.00231   0.0191   0.3879   0.0212
  -1.250  -0.0270   0.00992   0.00221   0.0194   0.3842   0.0357
  -1.000  -0.0011   0.00974   0.00213   0.0198   0.3802   0.0639
  -0.750   0.0235   0.00947   0.00205   0.0203   0.3757   0.1235
  -0.500   0.0357   0.00832   0.00184   0.0229   0.3718   0.4101
  -0.250   0.0269   0.00655   0.00175   0.0304   0.3696   0.8463
   0.000   0.0538   0.00671   0.00191   0.0309   0.3664   0.8738
   0.250   0.0815   0.00687   0.00204   0.0311   0.3629   0.8834
   0.500   0.1084   0.00707   0.00219   0.0316   0.3592   0.8937
   0.750   0.1360   0.00729   0.00238   0.0319   0.3553   0.8989
   1.000   0.1633   0.00746   0.00252   0.0322   0.3525   0.9046
   1.250   0.1911   0.00755   0.00257   0.0323   0.3493   0.9079
   1.500   0.2196   0.00758   0.00256   0.0321   0.3461   0.9087
   1.750   0.2480   0.00763   0.00256   0.0320   0.3425   0.9093
   2.000   0.2764   0.00769   0.00258   0.0318   0.3392   0.9099
   2.250   0.3050   0.00773   0.00259   0.0316   0.3368   0.9106
   2.500   0.3336   0.00777   0.00261   0.0314   0.3342   0.9111
   2.750   0.3622   0.00782   0.00263   0.0312   0.3314   0.9116
   3.000   0.3906   0.00788   0.00266   0.0309   0.3281   0.9121
   3.250   0.4188   0.00796   0.00271   0.0307   0.3248   0.9128
   3.500   0.4473   0.00801   0.00275   0.0305   0.3224   0.9135
   3.750   0.4759   0.00806   0.00279   0.0302   0.3197   0.9141
   4.000   0.5044   0.00812   0.00284   0.0300   0.3167   0.9146
   4.250   0.5328   0.00818   0.00289   0.0297   0.3140   0.9151
   4.500   0.5610   0.00827   0.00295   0.0295   0.3109   0.9157
   4.750   0.5894   0.00835   0.00302   0.0292   0.3081   0.9163
   5.000   0.6179   0.00840   0.00309   0.0289   0.3054   0.9168
   5.250   0.6464   0.00847   0.00316   0.0285   0.3023   0.9173
   5.500   0.6747   0.00856   0.00324   0.0282   0.2990   0.9179
   5.750   0.7028   0.00867   0.00334   0.0279   0.2957   0.9186
   6.000   0.7310   0.00876   0.00343   0.0276   0.2926   0.9193
   6.250   0.7594   0.00884   0.00353   0.0273   0.2893   0.9198
   6.500   0.7877   0.00894   0.00363   0.0269   0.2853   0.9203
   6.750   0.8157   0.00907   0.00375   0.0266   0.2811   0.9208
   7.000   0.8438   0.00918   0.00387   0.0263   0.2777   0.9213
   7.250   0.8721   0.00928   0.00399   0.0259   0.2735   0.9217
   7.500   0.8999   0.00943   0.00412   0.0256   0.2680   0.9221
   7.750   0.9276   0.00957   0.00428   0.0252   0.2635   0.9225
   8.000   0.9554   0.00970   0.00442   0.0249   0.2584   0.9230
   8.250   0.9821   0.00988   0.00459   0.0248   0.2516   0.9236
   8.500   1.0091   0.01003   0.00476   0.0246   0.2456   0.9241
   8.750   1.0354   0.01025   0.00497   0.0244   0.2380   0.9247
   9.000   1.0619   0.01044   0.00517   0.0243   0.2311   0.9253
   9.250   1.0873   0.01072   0.00543   0.0242   0.2217   0.9259
   9.500   1.1131   0.01097   0.00569   0.0242   0.2129   0.9265
   9.750   1.1382   0.01127   0.00597   0.0242   0.2039   0.9271
  10.000   1.1622   0.01165   0.00632   0.0243   0.1921   0.9279
  10.250   1.1857   0.01205   0.00670   0.0244   0.1809   0.9288
  10.500   1.2087   0.01250   0.00711   0.0246   0.1684   0.9297
  10.750   1.2306   0.01304   0.00760   0.0249   0.1542   0.9305
  11.000   1.2520   0.01358   0.00810   0.0252   0.1416   0.9314
  11.250   1.2724   0.01419   0.00867   0.0257   0.1286   0.9323
  11.750   1.3108   0.01549   0.00990   0.0267   0.1051   0.9343
  12.000   1.3286   0.01620   0.01059   0.0273   0.0950   0.9353
  12.250   1.3439   0.01694   0.01132   0.0282   0.0857   0.9364
  12.500   1.3572   0.01778   0.01215   0.0292   0.0776   0.9376
  12.750   1.3672   0.01878   0.01315   0.0305   0.0703   0.9392
  13.000   1.3763   0.01989   0.01430   0.0316   0.0637   0.9409
  13.250   1.3819   0.02144   0.01587   0.0322   0.0569   0.9429
  13.500   1.3853   0.02349   0.01794   0.0322   0.0506   0.9451
  13.750   1.3904   0.02566   0.02017   0.0316   0.0457   0.9474
  14.000   1.3924   0.02834   0.02289   0.0307   0.0415   0.9496
  14.500   1.3884   0.03445   0.02913   0.0291   0.0350   0.9534
  14.750   1.3837   0.03768   0.03245   0.0285   0.0325   0.9557
  15.000   1.3735   0.04159   0.03642   0.0278   0.0298   0.9581
  15.250   1.3658   0.04527   0.04019   0.0270   0.0282   0.9603
  15.500   1.3562   0.04924   0.04424   0.0260   0.0262   0.9623
  15.750   1.3414   0.05315   0.04823   0.0261   0.0248   0.9652
  16.000   1.3259   0.05714   0.05230   0.0262   0.0236   0.9687
  16.500   1.2962   0.06438   0.05970   0.0277   0.0216   0.9847
  16.750   1.2864   0.06861   0.06399   0.0266   0.0203   0.9908
  17.000   1.2769   0.07281   0.06825   0.0255   0.0191   0.9952
  17.250   1.2700   0.07684   0.07236   0.0240   0.0182   0.9980
  17.500   1.2624   0.08113   0.07673   0.0223   0.0170   1.0000
  17.750   1.2548   0.08543   0.08108   0.0207   0.0160   1.0000
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