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EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 341 AIRFOIL (e341-il)
Reynolds number: 500,000
Max Cl/Cd: 80.67 at α=10.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e341-il-500000-n5.txt
Download as CSV file: xf-e341-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5466   0.07160   0.06850  -0.0172   0.6715   0.0078
  -8.750  -0.5627   0.06675   0.06351  -0.0170   0.6608   0.0077
  -8.500  -0.5758   0.06218   0.05876  -0.0155   0.6502   0.0076
  -8.250  -0.5828   0.05735   0.05373  -0.0139   0.6401   0.0075
  -7.250  -0.6086   0.02772   0.02189   0.0022   0.6118   0.0066
  -7.000  -0.5924   0.02535   0.01914   0.0041   0.6005   0.0065
  -6.750  -0.5730   0.02338   0.01681   0.0055   0.5892   0.0065
  -6.500  -0.5513   0.02180   0.01491   0.0067   0.5779   0.0065
  -6.250  -0.5279   0.02050   0.01334   0.0075   0.5663   0.0065
  -6.000  -0.5035   0.01936   0.01198   0.0082   0.5557   0.0065
  -5.750  -0.4784   0.01842   0.01084   0.0088   0.5462   0.0066
  -5.500  -0.4530   0.01758   0.00984   0.0094   0.5364   0.0066
  -5.250  -0.4276   0.01676   0.00888   0.0099   0.5277   0.0066
  -5.000  -0.4027   0.01599   0.00799   0.0105   0.5183   0.0067
  -4.750  -0.3780   0.01532   0.00724   0.0111   0.5094   0.0069
  -4.500  -0.3531   0.01482   0.00665   0.0117   0.5003   0.0070
  -4.250  -0.3279   0.01438   0.00615   0.0123   0.4922   0.0072
  -4.000  -0.3028   0.01400   0.00570   0.0129   0.4844   0.0075
  -3.750  -0.2775   0.01364   0.00529   0.0134   0.4774   0.0078
  -3.500  -0.2522   0.01332   0.00490   0.0140   0.4699   0.0081
  -3.250  -0.2267   0.01304   0.00455   0.0145   0.4630   0.0087
  -3.000  -0.2013   0.01277   0.00422   0.0150   0.4556   0.0092
  -2.750  -0.1758   0.01254   0.00394   0.0155   0.4491   0.0102
  -2.500  -0.1499   0.01234   0.00370   0.0160   0.4429   0.0114
  -2.250  -0.1243   0.01214   0.00347   0.0165   0.4369   0.0140
  -2.000  -0.0987   0.01193   0.00328   0.0170   0.4317   0.0213
  -1.750  -0.0733   0.01170   0.00311   0.0174   0.4261   0.0383
  -1.500  -0.0483   0.01149   0.00297   0.0180   0.4204   0.0659
  -1.250  -0.0243   0.01118   0.00285   0.0186   0.4153   0.1213
  -1.000  -0.0152   0.00979   0.00257   0.0216   0.4110   0.4237
  -0.750  -0.0185   0.00852   0.00304   0.0289   0.4075   0.8527
  -0.500   0.0030   0.00878   0.00322   0.0306   0.4031   0.8788
  -0.250   0.0272   0.00903   0.00340   0.0317   0.3992   0.8916
   0.000   0.0592   0.00955   0.00388   0.0316   0.3945   0.9006
   0.250   0.0847   0.00985   0.00410   0.0326   0.3899   0.9092
   0.500   0.1216   0.01034   0.00451   0.0314   0.3853   0.9141
   0.750   0.1503   0.01049   0.00461   0.0314   0.3814   0.9181
   1.000   0.1724   0.01046   0.00452   0.0325   0.3778   0.9209
   1.250   0.1956   0.01044   0.00444   0.0333   0.3742   0.9231
   1.500   0.2238   0.01049   0.00442   0.0332   0.3705   0.9238
   1.750   0.2524   0.01051   0.00440   0.0330   0.3670   0.9245
   2.000   0.2808   0.01055   0.00440   0.0328   0.3634   0.9252
   2.250   0.3086   0.01059   0.00440   0.0328   0.3600   0.9259
   2.500   0.3360   0.01065   0.00441   0.0327   0.3566   0.9268
   2.750   0.3635   0.01070   0.00443   0.0327   0.3534   0.9277
   3.000   0.3906   0.01073   0.00444   0.0327   0.3504   0.9286
   3.250   0.4173   0.01076   0.00446   0.0329   0.3474   0.9296
   3.500   0.4436   0.01082   0.00449   0.0330   0.3444   0.9308
   3.750   0.4691   0.01088   0.00451   0.0333   0.3413   0.9320
   4.000   0.4944   0.01092   0.00455   0.0337   0.3384   0.9331
   4.250   0.5199   0.01094   0.00457   0.0340   0.3356   0.9342
   4.500   0.5450   0.01097   0.00460   0.0343   0.3324   0.9355
   4.750   0.5697   0.01102   0.00464   0.0348   0.3292   0.9369
   5.000   0.5952   0.01109   0.00470   0.0350   0.3264   0.9378
   5.250   0.6220   0.01118   0.00478   0.0350   0.3236   0.9383
   5.500   0.6494   0.01123   0.00486   0.0349   0.3207   0.9388
   5.750   0.6765   0.01130   0.00496   0.0348   0.3174   0.9393
   6.000   0.7033   0.01139   0.00506   0.0347   0.3140   0.9399
   6.250   0.7296   0.01151   0.00516   0.0348   0.3108   0.9406
   6.500   0.7560   0.01162   0.00530   0.0348   0.3079   0.9412
   6.750   0.7828   0.01170   0.00543   0.0347   0.3045   0.9421
   7.000   0.8091   0.01180   0.00556   0.0348   0.3006   0.9430
   7.250   0.8350   0.01193   0.00570   0.0348   0.2968   0.9438
   7.500   0.8605   0.01207   0.00585   0.0349   0.2932   0.9446
   7.750   0.8869   0.01216   0.00600   0.0349   0.2894   0.9455
   8.000   0.9127   0.01228   0.00616   0.0349   0.2851   0.9463
   8.250   0.9378   0.01244   0.00633   0.0350   0.2804   0.9473
   8.500   0.9636   0.01258   0.00651   0.0350   0.2759   0.9482
   8.750   0.9893   0.01272   0.00671   0.0350   0.2709   0.9491
   9.000   1.0140   0.01293   0.00691   0.0351   0.2651   0.9500
   9.250   1.0399   0.01309   0.00713   0.0350   0.2591   0.9508
   9.500   1.0644   0.01331   0.00738   0.0351   0.2525   0.9516
   9.750   1.0887   0.01352   0.00764   0.0353   0.2460   0.9524
  10.000   1.1117   0.01380   0.00793   0.0356   0.2377   0.9534
  10.250   1.1350   0.01407   0.00824   0.0359   0.2296   0.9545
  10.500   1.1570   0.01442   0.00860   0.0363   0.2212   0.9557
  10.750   1.1785   0.01480   0.00900   0.0367   0.2107   0.9569
  11.000   1.1994   0.01521   0.00943   0.0372   0.2003   0.9582
  11.250   1.2189   0.01570   0.00993   0.0378   0.1896   0.9597
  11.500   1.2368   0.01630   0.01052   0.0385   0.1772   0.9613
  11.750   1.2522   0.01697   0.01118   0.0395   0.1646   0.9630
  12.000   1.2629   0.01768   0.01189   0.0412   0.1537   0.9650
  12.250   1.2730   0.01856   0.01277   0.0428   0.1422   0.9676
  12.500   1.2822   0.01958   0.01382   0.0440   0.1313   0.9705
  12.750   1.2894   0.02083   0.01509   0.0450   0.1214   0.9735
  13.000   1.2944   0.02241   0.01670   0.0456   0.1125   0.9774
  13.250   1.2986   0.02443   0.01876   0.0454   0.1042   0.9816
  13.500   1.3038   0.02663   0.02101   0.0446   0.0964   0.9869
  13.750   1.3060   0.02939   0.02382   0.0433   0.0893   0.9922
  14.000   1.3070   0.03254   0.02703   0.0415   0.0824   0.9962
  14.250   1.3044   0.03572   0.03028   0.0401   0.0776   1.0000
  14.500   1.2993   0.03919   0.03382   0.0390   0.0729   1.0000
  14.750   1.2915   0.04303   0.03773   0.0377   0.0692   1.0000
  15.000   1.2855   0.04666   0.04143   0.0365   0.0654   1.0000
  15.250   1.2752   0.05080   0.04563   0.0352   0.0619   1.0000
  15.500   1.2648   0.05496   0.04986   0.0339   0.0589   1.0000
  15.750   1.2569   0.05895   0.05392   0.0326   0.0556   1.0000
  16.000   1.2467   0.06331   0.05833   0.0312   0.0524   1.0000
  16.250   1.2377   0.06761   0.06269   0.0297   0.0496   1.0000
  16.500   1.2303   0.07173   0.06688   0.0282   0.0468   1.0000
  16.750   1.2213   0.07613   0.07133   0.0267   0.0442   1.0000
  17.000   1.2135   0.08044   0.07569   0.0252   0.0418   1.0000
  17.250   1.2085   0.08437   0.07969   0.0237   0.0395   1.0000
  17.500   1.2008   0.08872   0.08410   0.0221   0.0373   1.0000
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