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EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E662 AIRFOIL (e662-il)
Reynolds number: 50,000
Max Cl/Cd: 23.39 at α=11°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e662-il-50000-n5.txt
Download as CSV file: xf-e662-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E662 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3404   0.11881   0.11214  -0.0672   0.9652   0.0590
  -9.750  -0.3350   0.11541   0.10874  -0.0677   0.9628   0.0578
  -9.500  -0.3333   0.11161   0.10496  -0.0692   0.9607   0.0567
  -9.250  -0.3363   0.10776   0.10113  -0.0706   0.9583   0.0558
  -9.000  -0.3448   0.10426   0.09770  -0.0709   0.9548   0.0550
  -8.750  -0.3533   0.10012   0.09361  -0.0724   0.9514   0.0544
  -8.500  -0.3641   0.09530   0.08882  -0.0751   0.9483   0.0536
  -8.250  -0.3822   0.09041   0.08394  -0.0775   0.9448   0.0527
  -8.000  -0.4127   0.08698   0.08053  -0.0759   0.9396   0.0517
  -7.750  -0.4404   0.08169   0.07512  -0.0766   0.9350   0.0502
  -7.500  -0.4523   0.07688   0.07008  -0.0775   0.9315   0.0498
  -7.250  -0.4663   0.07379   0.06686  -0.0750   0.9269   0.0498
  -7.000  -0.4676   0.07092   0.06384  -0.0739   0.9233   0.0505
  -6.750  -0.4635   0.06765   0.06035  -0.0738   0.9201   0.0513
  -6.500  -0.4541   0.06404   0.05641  -0.0744   0.9173   0.0522
  -6.250  -0.4523   0.06100   0.05305  -0.0728   0.9136   0.0523
  -6.000  -0.4440   0.05780   0.04945  -0.0720   0.9101   0.0524
  -5.750  -0.4285   0.05468   0.04585  -0.0719   0.9070   0.0526
  -5.500  -0.4071   0.05180   0.04248  -0.0724   0.9044   0.0532
  -5.250  -0.3812   0.04927   0.03945  -0.0732   0.9023   0.0542
  -5.000  -0.3639   0.04752   0.03730  -0.0723   0.8989   0.0559
  -4.750  -0.3436   0.04591   0.03519  -0.0714   0.8955   0.0588
  -4.500  -0.3196   0.04440   0.03338  -0.0713   0.8924   0.0610
  -4.250  -0.2931   0.04317   0.03201  -0.0714   0.8897   0.0633
  -4.000  -0.2638   0.04217   0.03080  -0.0717   0.8873   0.0662
  -3.750  -0.2437   0.04142   0.02986  -0.0703   0.8837   0.0699
  -3.500  -0.2248   0.04079   0.02917  -0.0688   0.8797   0.0755
  -3.250  -0.2010   0.04028   0.02854  -0.0682   0.8762   0.0830
  -3.000  -0.1738   0.03966   0.02787  -0.0681   0.8731   0.0928
  -2.750  -0.1487   0.03912   0.02732  -0.0680   0.8699   0.1131
  -2.500  -0.1344   0.03850   0.02688  -0.0664   0.8648   0.1440
  -2.250  -0.1116   0.03727   0.02644  -0.0669   0.8610   0.2495
  -2.000  -0.1074   0.03587   0.02719  -0.0613   0.8576   0.5836
  -1.750  -0.1076   0.03669   0.02815  -0.0538   0.8521   0.7655
  -1.500  -0.1019   0.03730   0.02857  -0.0484   0.8463   0.8266
  -1.250  -0.0921   0.03773   0.02883  -0.0430   0.8421   0.8751
  -1.000  -0.0794   0.03795   0.02888  -0.0387   0.8369   0.9158
  -0.750   0.1280   0.03991   0.02996  -0.0715   0.8422   0.9972
  -0.500   0.1415   0.04012   0.03001  -0.0702   0.8360   1.0000
  -0.250   0.1531   0.04025   0.02998  -0.0683   0.8295   1.0000
   0.000   0.1781   0.04043   0.02997  -0.0685   0.8255   1.0000
   0.250   0.1735   0.04055   0.03002  -0.0640   0.8163   1.0000
   0.500   0.1955   0.04073   0.03005  -0.0636   0.8114   1.0000
   0.750   0.1964   0.04088   0.03012  -0.0599   0.8029   1.0000
   1.000   0.2148   0.04104   0.03016  -0.0589   0.7972   1.0000
   1.250   0.2214   0.04121   0.03025  -0.0561   0.7894   1.0000
   1.500   0.2365   0.04137   0.03032  -0.0546   0.7826   1.0000
   1.750   0.2492   0.04158   0.03044  -0.0528   0.7757   1.0000
   2.000   0.2632   0.04180   0.03058  -0.0512   0.7681   1.0000
   2.250   0.2857   0.04206   0.03076  -0.0510   0.7623   1.0000
   2.500   0.2987   0.04239   0.03104  -0.0495   0.7537   1.0000
   2.750   0.3319   0.04263   0.03120  -0.0508   0.7495   1.0000
   3.000   0.3406   0.04309   0.03163  -0.0489   0.7391   1.0000
   3.500   0.3865   0.04384   0.03231  -0.0490   0.7243   1.0000
   3.750   0.4090   0.04425   0.03270  -0.0490   0.7166   1.0000
   4.000   0.4353   0.04457   0.03301  -0.0494   0.7093   1.0000
   4.250   0.4542   0.04509   0.03353  -0.0491   0.7001   1.0000
   4.500   0.4860   0.04527   0.03373  -0.0501   0.6941   1.0000
   4.750   0.5028   0.04587   0.03435  -0.0496   0.6837   1.0000
   5.000   0.5385   0.04589   0.03439  -0.0509   0.6788   1.0000
   5.500   0.5752   0.04705   0.03566  -0.0501   0.6578   1.0000
   5.750   0.6072   0.04709   0.03575  -0.0510   0.6511   1.0000
   6.000   0.6248   0.04775   0.03647  -0.0505   0.6398   1.0000
   6.250   0.6621   0.04745   0.03627  -0.0518   0.6348   1.0000
   6.500   0.6780   0.04819   0.03710  -0.0511   0.6226   1.0000
   6.750   0.6974   0.04878   0.03777  -0.0508   0.6113   1.0000
   7.000   0.7343   0.04829   0.03739  -0.0517   0.6056   1.0000
   7.250   0.7513   0.04899   0.03822  -0.0511   0.5930   1.0000
   7.500   0.7713   0.04951   0.03885  -0.0507   0.5814   1.0000
   7.750   0.8091   0.04867   0.03814  -0.0514   0.5756   1.0000
   8.000   0.8270   0.04926   0.03888  -0.0507   0.5627   1.0000
   8.250   0.8473   0.04965   0.03940  -0.0502   0.5505   1.0000
   8.500   0.8878   0.04827   0.03819  -0.0506   0.5449   1.0000
   8.750   0.9071   0.04868   0.03873  -0.0499   0.5314   1.0000
   9.000   0.9280   0.04893   0.03916  -0.0493   0.5181   1.0000
   9.250   0.9513   0.04896   0.03935  -0.0487   0.5051   1.0000
   9.500   0.9777   0.04867   0.03921  -0.0482   0.4922   1.0000
   9.750   1.0057   0.04820   0.03892  -0.0478   0.4787   1.0000
  10.000   1.0320   0.04789   0.03876  -0.0472   0.4637   1.0000
  10.250   1.0558   0.04780   0.03879  -0.0465   0.4470   1.0000
  10.500   1.0791   0.04777   0.03887  -0.0457   0.4291   1.0000
  10.750   1.1034   0.04764   0.03885  -0.0449   0.4103   1.0000
  11.000   1.1229   0.04800   0.03927  -0.0440   0.3904   1.0000
  11.250   1.1348   0.04908   0.04043  -0.0428   0.3693   1.0000
  11.500   1.1511   0.04974   0.04110  -0.0417   0.3484   1.0000
  11.750   1.1603   0.05113   0.04254  -0.0404   0.3277   1.0000
  12.000   1.1684   0.05266   0.04413  -0.0392   0.3071   1.0000
  12.250   1.1776   0.05409   0.04554  -0.0381   0.2874   1.0000
  12.500   1.1822   0.05610   0.04759  -0.0370   0.2683   1.0000
  12.750   1.1861   0.05823   0.04978  -0.0359   0.2499   1.0000
  13.000   1.1897   0.06045   0.05202  -0.0350   0.2324   1.0000
  13.250   1.1929   0.06279   0.05438  -0.0342   0.2161   1.0000
  13.500   1.1953   0.06529   0.05691  -0.0335   0.2008   1.0000
  13.750   1.1970   0.06798   0.05966  -0.0330   0.1863   1.0000
  14.000   1.1987   0.07077   0.06252  -0.0325   0.1730   1.0000
  14.250   1.1993   0.07376   0.06558  -0.0323   0.1605   1.0000
  14.500   1.2003   0.07678   0.06868  -0.0321   0.1492   1.0000
  14.750   1.2016   0.07979   0.07171  -0.0320   0.1389   1.0000
  15.000   1.2021   0.08300   0.07499  -0.0321   0.1291   1.0000
  15.250   1.2016   0.08656   0.07874  -0.0324   0.1201   1.0000
  15.500   1.2024   0.08980   0.08200  -0.0327   0.1121   1.0000
  15.750   1.2005   0.09363   0.08601  -0.0334   0.1045   1.0000
  16.000   1.1996   0.09737   0.08987  -0.0341   0.0977   1.0000
  16.250   1.1967   0.10141   0.09407  -0.0351   0.0912   1.0000
  16.500   1.1941   0.10555   0.09834  -0.0363   0.0855   1.0000
  16.750   1.1878   0.11040   0.10339  -0.0380   0.0802   1.0000
  17.000   1.1871   0.11412   0.10710  -0.0393   0.0750   1.0000
  17.250   1.1753   0.12042   0.11374  -0.0421   0.0713   1.0000
  17.500   1.1705   0.12517   0.11858  -0.0444   0.0670   1.0000
  17.750   1.1663   0.12989   0.12336  -0.0467   0.0633   1.0000
  18.000   1.1495   0.13787   0.13166  -0.0511   0.0614   1.0000
  18.250   1.1299   0.14686   0.14092  -0.0563   0.0601   1.0000
  18.500   1.1015   0.15885   0.15312  -0.0637   0.0601   1.0000
  18.750   1.0624   0.17559   0.16987  -0.0739   0.0610   1.0000
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