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EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 417 AIRFOIL (e417-il)
Reynolds number: 100,000
Max Cl/Cd: 46.76 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e417-il-100000.txt
Download as CSV file: xf-e417-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 417 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6012   0.10688   0.10249  -0.0406   1.0000   0.1495
  -9.250  -0.5292   0.10650   0.10196  -0.0316   1.0000   0.1545
  -7.000  -0.7326   0.05327   0.04730  -0.0439   1.0000   0.0880
  -6.750  -0.7109   0.04543   0.03831  -0.0443   1.0000   0.0618
  -6.500  -0.6902   0.04132   0.03373  -0.0443   1.0000   0.0574
  -6.250  -0.6649   0.03827   0.02986  -0.0442   1.0000   0.0538
  -6.000  -0.6431   0.03588   0.02729  -0.0439   1.0000   0.0551
  -5.750  -0.6205   0.03406   0.02526  -0.0434   1.0000   0.0559
  -5.500  -0.5977   0.03238   0.02338  -0.0425   1.0000   0.0558
  -5.250  -0.5755   0.03089   0.02176  -0.0413   1.0000   0.0561
  -5.000  -0.5539   0.02966   0.02047  -0.0400   1.0000   0.0569
  -4.750  -0.5325   0.02859   0.01940  -0.0388   1.0000   0.0585
  -4.500  -0.5108   0.02768   0.01848  -0.0378   1.0000   0.0610
  -4.250  -0.4878   0.02695   0.01769  -0.0371   1.0000   0.0648
  -4.000  -0.4622   0.02588   0.01675  -0.0378   1.0000   0.0742
  -3.750  -0.4308   0.02471   0.01567  -0.0396   1.0000   0.0955
  -3.500  -0.4001   0.02398   0.01765  -0.0402   1.0000   0.5991
  -3.250  -0.3961   0.02582   0.01949  -0.0333   1.0000   0.6295
  -3.000  -0.3973   0.02766   0.02139  -0.0249   1.0000   0.6539
  -2.750  -0.4027   0.02940   0.02321  -0.0153   1.0000   0.6773
  -2.500  -0.4021   0.03075   0.02455  -0.0077   1.0000   0.7034
  -2.250  -0.4048   0.03156   0.02538   0.0005   1.0000   0.7209
  -2.000  -0.4001   0.03197   0.02575   0.0060   1.0000   0.7372
  -1.750  -0.3859   0.03204   0.02569   0.0084   1.0000   0.7505
  -1.500  -0.3688   0.03196   0.02549   0.0097   1.0000   0.7587
  -1.250  -0.3470   0.03179   0.02519   0.0094   1.0000   0.7656
  -1.000  -0.3280   0.03168   0.02498   0.0100   1.0000   0.7715
  -0.750  -0.2972   0.03167   0.02480   0.0070   1.0000   0.7777
  -0.500  -0.2815   0.03154   0.02461   0.0084   1.0000   0.7817
  -0.250  -0.2596   0.03155   0.02454   0.0079   1.0000   0.7863
   0.000  -0.2312   0.03168   0.02456   0.0056   1.0000   0.7910
   0.250  -0.1450   0.03353   0.02620  -0.0063   0.9681   0.7948
   0.500  -0.1043   0.03385   0.02644  -0.0097   0.9548   0.7987
   0.750  -0.0622   0.03414   0.02664  -0.0136   0.9435   0.8024
   1.000  -0.0115   0.03464   0.02706  -0.0195   0.9349   0.8065
   1.250   0.0194   0.03453   0.02693  -0.0210   0.9233   0.8096
   1.500   0.0518   0.03454   0.02692  -0.0227   0.9123   0.8129
   1.750   0.0904   0.03467   0.02703  -0.0257   0.9026   0.8168
   2.000   0.1368   0.03484   0.02719  -0.0302   0.8942   0.8203
   2.250   0.1691   0.03474   0.02711  -0.0320   0.8828   0.8235
   2.500   0.2012   0.03467   0.02708  -0.0334   0.8724   0.8269
   2.750   0.2474   0.03466   0.02710  -0.0372   0.8656   0.8306
   3.000   0.2809   0.03458   0.02707  -0.0393   0.8540   0.8339
   3.250   0.3170   0.03450   0.02705  -0.0416   0.8433   0.8373
   3.500   0.3617   0.03408   0.02673  -0.0444   0.8370   0.8408
   3.750   0.3940   0.03375   0.02647  -0.0456   0.8245   0.8444
   4.000   0.4312   0.03336   0.02618  -0.0476   0.8124   0.8478
   4.250   0.4727   0.03286   0.02581  -0.0502   0.8015   0.8514
   4.500   0.5173   0.03186   0.02495  -0.0522   0.7944   0.8551
   4.750   0.5512   0.03120   0.02441  -0.0530   0.7817   0.8590
   5.000   0.5904   0.03039   0.02377  -0.0547   0.7695   0.8626
   5.250   0.6462   0.02867   0.02225  -0.0581   0.7635   0.8664
   5.500   0.6818   0.02732   0.02110  -0.0581   0.7510   0.8705
   5.750   0.7215   0.02588   0.01985  -0.0588   0.7377   0.8748
   6.000   0.7699   0.02418   0.01837  -0.0609   0.7229   0.8788
   6.250   0.8180   0.02238   0.01677  -0.0625   0.7030   0.8825
   6.500   0.8601   0.02111   0.01564  -0.0635   0.6717   0.8870
   6.750   0.9041   0.02027   0.01483  -0.0651   0.6257   0.8917
   7.000   0.9367   0.02007   0.01449  -0.0652   0.5678   0.8960
   7.250   0.9529   0.02038   0.01457  -0.0628   0.5056   0.9007
   7.500   0.9622   0.02111   0.01495  -0.0597   0.4369   0.9060
   7.750   0.9658   0.02200   0.01547  -0.0558   0.3704   0.9116
   8.000   0.9689   0.02303   0.01619  -0.0523   0.3052   0.9181
   8.250   0.9736   0.02420   0.01704  -0.0493   0.2448   0.9246
   8.500   0.9767   0.02564   0.01811  -0.0462   0.1802   0.9317
   8.750   0.9722   0.02804   0.01985  -0.0424   0.1069   0.9388
   9.000   0.9729   0.03026   0.02182  -0.0389   0.0745   0.9478
   9.250   0.9810   0.03201   0.02355  -0.0366   0.0641   0.9596
   9.500   0.9962   0.03348   0.02503  -0.0354   0.0579   0.9926
   9.750   1.0321   0.03583   0.02741  -0.0371   0.0529   1.0000
  10.000   1.0664   0.03783   0.02952  -0.0388   0.0483   1.0000
  10.250   1.1237   0.04174   0.03340  -0.0438   0.0446   1.0000
  10.500   1.1601   0.04504   0.03711  -0.0457   0.0438   1.0000
  10.750   1.1860   0.04875   0.04127  -0.0464   0.0435   1.0000
  11.000   1.2020   0.05269   0.04569  -0.0459   0.0436   1.0000
  11.250   1.2103   0.05684   0.05025  -0.0446   0.0439   1.0000
  11.500   1.2140   0.06137   0.05513  -0.0432   0.0443   1.0000
  11.750   1.2204   0.06690   0.06098  -0.0426   0.0450   1.0000
  12.000   1.2116   0.06909   0.06353  -0.0396   0.0456   1.0000
  12.250   1.1848   0.07230   0.06725  -0.0356   0.0467   1.0000
  12.500   1.1402   0.07778   0.07329  -0.0324   0.0482   1.0000
  12.750   1.1065   0.08396   0.07984  -0.0319   0.0493   1.0000
  13.000   1.0757   0.09062   0.08677  -0.0331   0.0502   1.0000
  13.250   1.0448   0.09809   0.09444  -0.0362   0.0510   1.0000
  13.500   1.0136   0.10673   0.10326  -0.0411   0.0518   1.0000
  13.750   0.9829   0.11695   0.11361  -0.0481   0.0527   1.0000
  14.000   0.9630   0.12691   0.12363  -0.0547   0.0541   1.0000
  14.250   0.9108   0.15153   0.14823  -0.0706   0.0660   1.0000
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