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GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il)
Reynolds number: 200,000
Max Cl/Cd: 80.78 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe238-il-200000-n5.txt
Download as CSV file: xf-goe238-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 238 (HANSA-BRANDENBURG) AIRFOIL             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2161   0.09485   0.09025  -0.0444   0.7049   0.0341
  -8.500  -0.2161   0.09229   0.08767  -0.0466   0.6975   0.0342
  -8.250  -0.2043   0.08868   0.08405  -0.0462   0.6902   0.0345
  -8.000  -0.1921   0.08581   0.08113  -0.0458   0.6826   0.0349
  -7.750  -0.1839   0.08332   0.07862  -0.0460   0.6758   0.0355
  -7.500  -0.1779   0.08095   0.07625  -0.0466   0.6688   0.0363
  -7.250  -0.1748   0.07864   0.07391  -0.0473   0.6628   0.0367
  -7.000  -0.1702   0.07618   0.07144  -0.0487   0.6569   0.0374
  -6.750  -0.1625   0.07344   0.06868  -0.0509   0.6509   0.0383
  -6.500  -0.1532   0.07048   0.06564  -0.0552   0.6456   0.0396
  -6.250  -0.1388   0.06712   0.06218  -0.0610   0.6401   0.0400
  -6.000  -0.1209   0.06361   0.05850  -0.0655   0.6344   0.0402
  -5.750  -0.1099   0.06048   0.05537  -0.0646   0.6290   0.0406
  -5.500  -0.0959   0.05814   0.05304  -0.0641   0.6232   0.0412
  -5.250  -0.0793   0.05576   0.05060  -0.0648   0.6174   0.0419
  -5.000  -0.0607   0.05323   0.04797  -0.0661   0.6125   0.0426
  -4.750  -0.0404   0.05065   0.04529  -0.0676   0.6075   0.0437
  -4.500  -0.0179   0.04798   0.04249  -0.0693   0.6022   0.0451
  -4.250   0.0156   0.04473   0.03877  -0.0729   0.5977   0.0471
  -4.000   0.0392   0.04184   0.03559  -0.0737   0.5935   0.0473
  -3.750   0.0562   0.03931   0.03315  -0.0736   0.5879   0.0480
  -3.500   0.0765   0.03767   0.03148  -0.0736   0.5827   0.0489
  -3.250   0.0995   0.03588   0.02955  -0.0737   0.5782   0.0501
  -3.000   0.1308   0.03077   0.02373  -0.0740   0.5742   0.0401
  -2.750   0.1538   0.02914   0.02205  -0.0740   0.5692   0.0395
  -2.500   0.1783   0.02738   0.02010  -0.0738   0.5649   0.0389
  -2.250   0.2036   0.02558   0.01802  -0.0735   0.5612   0.0384
  -2.000   0.2299   0.02391   0.01607  -0.0731   0.5569   0.0388
  -1.750   0.2567   0.02246   0.01427  -0.0726   0.5525   0.0395
  -1.500   0.2829   0.02124   0.01280  -0.0722   0.5484   0.0393
  -1.250   0.3094   0.02017   0.01145  -0.0717   0.5449   0.0392
  -1.000   0.3363   0.01922   0.01030  -0.0714   0.5406   0.0393
  -0.750   0.3634   0.01841   0.00930  -0.0710   0.5362   0.0395
  -0.500   0.3905   0.01774   0.00842  -0.0706   0.5323   0.0399
  -0.250   0.4175   0.01717   0.00766  -0.0702   0.5290   0.0404
   0.000   0.4443   0.01671   0.00720  -0.0700   0.5256   0.0417
   0.250   0.4713   0.01640   0.00689  -0.0697   0.5218   0.0432
   0.500   0.4983   0.01601   0.00645  -0.0694   0.5181   0.0440
   0.750   0.5252   0.01565   0.00602  -0.0690   0.5145   0.0448
   1.000   0.5519   0.01535   0.00565  -0.0686   0.5110   0.0457
   1.250   0.5785   0.01509   0.00541  -0.0682   0.5064   0.0467
   1.500   0.6047   0.01482   0.00517  -0.0678   0.5021   0.0481
   1.750   0.6309   0.01466   0.00506  -0.0675   0.4984   0.0507
   2.000   0.6572   0.01457   0.00493  -0.0671   0.4951   0.0537
   2.250   0.6835   0.01445   0.00487  -0.0667   0.4911   0.0557
   2.500   0.7096   0.01433   0.00480  -0.0663   0.4874   0.0589
   2.750   0.7360   0.01431   0.00478  -0.0660   0.4841   0.0638
   3.000   0.7622   0.01427   0.00473  -0.0656   0.4812   0.0724
   3.500   0.8400   0.01255   0.00498  -0.0706   0.4734   1.0000
   3.750   0.8657   0.01269   0.00508  -0.0701   0.4694   1.0000
   4.000   0.8914   0.01285   0.00518  -0.0697   0.4661   1.0000
   4.250   0.9172   0.01303   0.00529  -0.0692   0.4632   1.0000
   4.500   0.9428   0.01320   0.00549  -0.0688   0.4597   1.0000
   4.750   0.9682   0.01336   0.00568  -0.0683   0.4552   1.0000
   5.000   0.9935   0.01350   0.00581  -0.0678   0.4501   1.0000
   5.250   1.0188   0.01366   0.00593  -0.0673   0.4451   1.0000
   5.500   1.0436   0.01380   0.00614  -0.0668   0.4378   1.0000
   5.750   1.0684   0.01394   0.00625  -0.0662   0.4313   1.0000
   6.000   1.0930   0.01409   0.00646  -0.0656   0.4229   1.0000
   6.250   1.1173   0.01425   0.00660  -0.0650   0.4149   1.0000
   6.500   1.1420   0.01444   0.00688  -0.0645   0.4078   1.0000
   6.750   1.1662   0.01464   0.00710  -0.0639   0.4007   1.0000
   7.000   1.1903   0.01485   0.00737  -0.0633   0.3922   1.0000
   7.250   1.2136   0.01507   0.00762  -0.0626   0.3821   1.0000
   7.500   1.2367   0.01531   0.00791  -0.0619   0.3686   1.0000
   7.750   1.2587   0.01559   0.00820  -0.0610   0.3504   1.0000
   8.000   1.2796   0.01595   0.00854  -0.0600   0.3267   1.0000
   8.250   1.2963   0.01654   0.00899  -0.0585   0.2924   1.0000
   8.500   1.3093   0.01741   0.00967  -0.0566   0.2631   1.0000
   8.750   1.3226   0.01827   0.01045  -0.0548   0.2443   1.0000
   9.000   1.3347   0.01917   0.01129  -0.0528   0.2287   1.0000
   9.500   1.3589   0.02083   0.01297  -0.0490   0.2053   1.0000
   9.750   1.3679   0.02169   0.01385  -0.0467   0.1942   1.0000
  10.000   1.3724   0.02268   0.01485  -0.0438   0.1791   1.0000
  10.250   1.3736   0.02396   0.01609  -0.0410   0.1565   1.0000
  10.500   1.3566   0.02676   0.01862  -0.0381   0.1124   1.0000
  10.750   1.3440   0.02985   0.02154  -0.0364   0.0899   1.0000
  11.000   1.3393   0.03251   0.02417  -0.0353   0.0807   1.0000
  11.250   1.3386   0.03491   0.02662  -0.0345   0.0756   1.0000
  11.500   1.3379   0.03737   0.02913  -0.0338   0.0718   1.0000
  11.750   1.3349   0.04013   0.03194  -0.0332   0.0685   1.0000
  12.000   1.3365   0.04249   0.03438  -0.0328   0.0658   1.0000
  12.250   1.3366   0.04503   0.03701  -0.0324   0.0631   1.0000
  12.500   1.3347   0.04782   0.03987  -0.0321   0.0610   1.0000
  12.750   1.3314   0.05084   0.04295  -0.0319   0.0590   1.0000
  13.000   1.3259   0.05413   0.04631  -0.0318   0.0573   1.0000
  13.250   1.3274   0.05671   0.04901  -0.0317   0.0558   1.0000
  13.500   1.3294   0.05934   0.05175  -0.0317   0.0540   1.0000
  13.750   1.3301   0.06219   0.05469  -0.0318   0.0523   1.0000
  14.000   1.3301   0.06518   0.05776  -0.0320   0.0507   1.0000
  14.250   1.3288   0.06838   0.06102  -0.0324   0.0491   1.0000
  14.500   1.3252   0.07188   0.06455  -0.0328   0.0475   1.0000
  14.750   1.3282   0.07464   0.06742  -0.0331   0.0459   1.0000
  15.000   1.3311   0.07745   0.07036  -0.0335   0.0441   1.0000
  15.250   1.3331   0.08044   0.07345  -0.0340   0.0421   1.0000
  15.500   1.3334   0.08368   0.07676  -0.0346   0.0406   1.0000
  15.750   1.3315   0.08722   0.08032  -0.0353   0.0391   1.0000
  16.000   1.3347   0.09018   0.08342  -0.0360   0.0372   1.0000
  16.250   1.3364   0.09333   0.08668  -0.0367   0.0355   1.0000
  16.500   1.3367   0.09679   0.09022  -0.0376   0.0339   1.0000
  16.750   1.3355   0.10047   0.09395  -0.0387   0.0327   1.0000
  17.000   1.3365   0.10381   0.09740  -0.0396   0.0312   1.0000
  17.250   1.3372   0.10728   0.10098  -0.0407   0.0295   1.0000
  17.500   1.3367   0.11101   0.10479  -0.0420   0.0282   1.0000
  17.750   1.3347   0.11502   0.10885  -0.0435   0.0271   1.0000
  18.000   1.3353   0.11851   0.11245  -0.0447   0.0261   1.0000
  18.250   1.3357   0.12210   0.11615  -0.0460   0.0249   1.0000
  18.500   1.3352   0.12589   0.12004  -0.0475   0.0240   1.0000
  18.750   1.3340   0.12986   0.12408  -0.0492   0.0232   1.0000
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