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EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 379 AIRFOIL (e379-il)
Reynolds number: 50,000
Max Cl/Cd: 40.57 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e379-il-50000-n5.txt
Download as CSV file: xf-e379-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 379 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2939   0.11455   0.10838  -0.0005   1.0000   0.0195
  -8.250  -0.2850   0.11322   0.10713  -0.0024   1.0000   0.0198
  -8.000  -0.2760   0.11203   0.10604  -0.0045   1.0000   0.0199
  -7.750  -0.2640   0.11186   0.10597  -0.0083   1.0000   0.0201
  -7.500  -0.2549   0.10526   0.09944  -0.0074   1.0000   0.0207
  -7.250  -0.2448   0.10150   0.09576  -0.0084   1.0000   0.0215
  -7.000  -0.2332   0.09868   0.09303  -0.0103   1.0000   0.0222
  -6.750  -0.2206   0.09611   0.09055  -0.0124   1.0000   0.0229
  -6.500  -0.2075   0.09362   0.08815  -0.0146   1.0000   0.0236
  -6.250  -0.1942   0.09125   0.08589  -0.0170   1.0000   0.0244
  -6.000  -0.1822   0.08916   0.08394  -0.0192   1.0000   0.0251
  -5.750  -0.1544   0.08633   0.08114  -0.0254   0.9691   0.0262
  -5.500  -0.1129   0.08371   0.07845  -0.0344   0.9374   0.0273
  -5.250  -0.0670   0.08247   0.07696  -0.0446   0.9099   0.0279
  -5.000  -0.0469   0.07765   0.07213  -0.0467   0.8890   0.0285
  -4.750  -0.0300   0.07362   0.06805  -0.0480   0.8692   0.0299
  -4.500  -0.0078   0.07087   0.06522  -0.0505   0.8503   0.0316
  -4.250   0.0164   0.06848   0.06273  -0.0534   0.8334   0.0336
  -4.000   0.0440   0.06652   0.06065  -0.0570   0.8176   0.0358
  -3.750   0.0828   0.06582   0.05977  -0.0628   0.8024   0.0373
  -3.500   0.1067   0.06292   0.05680  -0.0650   0.7898   0.0380
  -3.250   0.1231   0.05933   0.05316  -0.0654   0.7785   0.0403
  -3.000   0.1514   0.05711   0.05084  -0.0683   0.7665   0.0436
  -2.750   0.1969   0.05688   0.05036  -0.0741   0.7548   0.0469
  -2.500   0.2192   0.05349   0.04693  -0.0755   0.7449   0.0484
  -2.250   0.2427   0.05069   0.04404  -0.0769   0.7360   0.0521
  -2.000   0.2804   0.04952   0.04267  -0.0805   0.7261   0.0574
  -1.750   0.3113   0.04734   0.04038  -0.0830   0.7168   0.0598
  -1.500   0.3403   0.04534   0.03824  -0.0847   0.7089   0.0662
  -1.250   0.3736   0.04363   0.03627  -0.0872   0.7000   0.0714
  -1.000   0.4137   0.04349   0.03586  -0.0901   0.6915   0.0810
  -0.750   0.4436   0.04182   0.03402  -0.0915   0.6842   0.0933
  -0.500   0.4675   0.03903   0.03122  -0.0925   0.6762   0.1083
  -0.250   0.5006   0.03831   0.03023  -0.0939   0.6696   0.1308
   0.000   0.5269   0.03613   0.02802  -0.0950   0.6615   0.1475
   0.500   0.5858   0.03342   0.02501  -0.0969   0.6475   0.2006
   1.000   0.6427   0.03071   0.02187  -0.0982   0.6342   0.2810
   1.250   0.6911   0.03137   0.02183  -0.0982   0.6289   0.0757
   1.500   0.7240   0.03077   0.02089  -0.0984   0.6214   0.0576
   1.750   0.7530   0.02979   0.01966  -0.0983   0.6160   0.0538
   2.000   0.7851   0.02924   0.01879  -0.0989   0.6089   0.0522
   2.250   0.8175   0.02871   0.01782  -0.0990   0.6032   0.0594
   2.750   0.8792   0.02781   0.01624  -0.0995   0.5906   0.0732
   3.000   0.9067   0.02752   0.01568  -0.0992   0.5846   0.0770
   3.250   0.9324   0.02742   0.01537  -0.0987   0.5782   0.0818
   3.500   0.9576   0.02735   0.01519  -0.0980   0.5733   0.0907
   3.750   0.9823   0.02769   0.01557  -0.0980   0.5659   0.1238
   4.000   1.0117   0.02692   0.01557  -0.0983   0.5610   1.0000
   4.250   1.0356   0.02778   0.01625  -0.0983   0.5533   1.0000
   4.500   1.0604   0.02821   0.01649  -0.0976   0.5480   1.0000
   4.750   1.0835   0.02912   0.01740  -0.0975   0.5404   1.0000
   5.000   1.1080   0.02957   0.01781  -0.0968   0.5348   1.0000
   5.250   1.1303   0.03053   0.01885  -0.0966   0.5270   1.0000
   5.500   1.1547   0.03097   0.01947  -0.0959   0.5212   1.0000
   5.750   1.1762   0.03198   0.02061  -0.0957   0.5129   1.0000
   6.000   1.2008   0.03230   0.02096  -0.0948   0.5070   1.0000
   6.250   1.2212   0.03339   0.02224  -0.0945   0.4976   1.0000
   6.500   1.2446   0.03385   0.02283  -0.0937   0.4903   1.0000
   6.750   1.2665   0.03449   0.02365  -0.0929   0.4814   1.0000
   7.000   1.2867   0.03537   0.02476  -0.0923   0.4714   1.0000
   7.250   1.3098   0.03567   0.02525  -0.0912   0.4628   1.0000
   7.500   1.3324   0.03593   0.02628  -0.0899   0.4531   1.0000
   7.750   1.3518   0.03662   0.02733  -0.0890   0.4413   1.0000
   8.000   1.3719   0.03712   0.02817  -0.0878   0.4293   1.0000
   8.250   1.3923   0.03742   0.02883  -0.0865   0.4166   1.0000
   8.500   1.4130   0.03757   0.02937  -0.0850   0.4025   1.0000
   8.750   1.4287   0.03522   0.02708  -0.0814   0.3504   1.0000
   9.000   1.4394   0.03573   0.02778  -0.0794   0.3075   1.0000
   9.250   1.4460   0.03699   0.02909  -0.0773   0.2585   1.0000
   9.500   1.4332   0.04007   0.03138  -0.0752   0.1822   1.0000
   9.750   1.4158   0.04405   0.03498  -0.0738   0.1399   1.0000
  10.000   1.3983   0.04868   0.03936  -0.0736   0.1057   1.0000
  10.250   1.3809   0.05382   0.04424  -0.0741   0.0742   1.0000
  10.500   1.3667   0.05880   0.04904  -0.0747   0.0519   1.0000
  10.750   1.3526   0.06400   0.05411  -0.0753   0.0361   1.0000
  11.000   1.3421   0.06885   0.05899  -0.0759   0.0301   1.0000
  11.250   1.3327   0.07370   0.06396  -0.0765   0.0260   1.0000
  11.500   1.3231   0.07868   0.06904  -0.0773   0.0232   1.0000
  11.750   1.3149   0.08354   0.07405  -0.0781   0.0219   1.0000
  12.000   1.3053   0.08874   0.07931  -0.0791   0.0205   1.0000
  12.250   1.2990   0.09348   0.08427  -0.0800   0.0193   1.0000
  12.500   1.2937   0.09819   0.08921  -0.0809   0.0183   1.0000
  12.750   1.2891   0.10290   0.09413  -0.0818   0.0171   1.0000
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