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GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il)
Reynolds number: 50,000
Max Cl/Cd: 33.92 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe207-il-50000-n5.txt
Download as CSV file: xf-goe207-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 207 (AVIATIK V8) 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  -0.2495   0.11421   0.10787  -0.0160   1.0000   0.0655
  -8.250  -0.2479   0.11311   0.10687  -0.0183   1.0000   0.0660
  -8.000  -0.2470   0.11213   0.10601  -0.0210   1.0000   0.0662
  -7.750  -0.2346   0.10706   0.10103  -0.0200   1.0000   0.0670
  -7.500  -0.2255   0.10352   0.09756  -0.0200   1.0000   0.0680
  -7.250  -0.2189   0.10086   0.09500  -0.0207   1.0000   0.0692
  -7.000  -0.2147   0.09866   0.09293  -0.0214   1.0000   0.0703
  -6.750  -0.2155   0.09705   0.09148  -0.0215   1.0000   0.0714
  -6.500  -0.1950   0.09414   0.08860  -0.0273   0.9813   0.0733
  -6.250  -0.1553   0.09204   0.08639  -0.0413   0.9516   0.0754
  -6.000  -0.1309   0.08660   0.08097  -0.0435   0.9321   0.0769
  -5.750  -0.1044   0.08238   0.07670  -0.0467   0.9113   0.0797
  -5.500  -0.0766   0.07922   0.07344  -0.0518   0.8877   0.0828
  -5.250  -0.0413   0.07759   0.07159  -0.0606   0.8630   0.0860
  -5.000  -0.0162   0.07466   0.06852  -0.0644   0.8412   0.0871
  -4.750  -0.0035   0.07081   0.06465  -0.0630   0.8200   0.0889
  -4.500   0.0152   0.06803   0.06177  -0.0638   0.7993   0.0916
  -4.250   0.0391   0.06573   0.05932  -0.0663   0.7797   0.0954
  -3.750   0.0892   0.06090   0.05414  -0.0713   0.7437   0.1028
  -3.500   0.1114   0.05855   0.05165  -0.0724   0.7269   0.1087
  -3.250   0.1480   0.05726   0.05001  -0.0772   0.7102   0.1156
  -3.000   0.1654   0.05411   0.04684  -0.0767   0.6952   0.1194
  -2.750   0.2062   0.05396   0.04622  -0.0814   0.6793   0.1303
  -2.500   0.2220   0.05009   0.04241  -0.0806   0.6660   0.1341
  -2.250   0.2555   0.04891   0.04089  -0.0833   0.6521   0.1466
  -2.000   0.2772   0.04626   0.03821  -0.0835   0.6382   0.1548
  -1.750   0.3055   0.04446   0.03623  -0.0850   0.6244   0.1696
  -1.500   0.3332   0.04267   0.03426  -0.0864   0.6113   0.1944
  -1.250   0.3570   0.04063   0.03212  -0.0869   0.5994   0.2304
  -1.000   0.3799   0.03849   0.02992  -0.0873   0.5871   0.2791
  -0.750   0.4069   0.03670   0.02801  -0.0880   0.5744   0.3114
  -0.500   0.4386   0.03531   0.02640  -0.0894   0.5628   0.3258
   0.000   0.5294   0.03560   0.02546  -0.0930   0.5389   0.1534
   0.250   0.5681   0.03514   0.02438  -0.0929   0.5283   0.0977
   0.500   0.5978   0.03401   0.02301  -0.0932   0.5183   0.0922
   0.750   0.6283   0.03340   0.02214  -0.0935   0.5073   0.0894
   1.000   0.6591   0.03312   0.02140  -0.0932   0.4983   0.0864
   1.250   0.6871   0.03236   0.02055  -0.0934   0.4876   0.0847
   1.500   0.7156   0.03181   0.01979  -0.0933   0.4788   0.0830
   1.750   0.7439   0.03141   0.01920  -0.0932   0.4696   0.0817
   2.000   0.7717   0.03110   0.01865  -0.0928   0.4612   0.0810
   2.250   0.7993   0.03092   0.01823  -0.0924   0.4527   0.0824
   2.500   0.8266   0.03082   0.01787  -0.0919   0.4455   0.0853
   2.750   0.8529   0.03076   0.01770  -0.0914   0.4376   0.0872
   3.000   0.8792   0.03052   0.01728  -0.0907   0.4320   0.0889
   3.250   0.9042   0.03066   0.01745  -0.0903   0.4242   0.0912
   3.500   0.9300   0.03071   0.01739  -0.0899   0.4182   0.0960
   3.750   0.9559   0.03087   0.01747  -0.0896   0.4124   0.1035
   4.000   0.9812   0.03125   0.01784  -0.0894   0.4058   0.1114
   4.250   1.0078   0.03144   0.01796  -0.0893   0.4009   0.1255
   4.500   1.0338   0.03184   0.01842  -0.0892   0.3960   0.1561
   4.750   1.0537   0.03121   0.01907  -0.0881   0.3910   1.0000
   5.000   1.0787   0.03194   0.01954  -0.0876   0.3867   1.0000
   5.250   1.1045   0.03256   0.01995  -0.0873   0.3834   1.0000
   5.500   1.1267   0.03369   0.02110  -0.0870   0.3790   1.0000
   5.750   1.1483   0.03483   0.02229  -0.0867   0.3745   1.0000
   6.000   1.1716   0.03571   0.02317  -0.0864   0.3708   1.0000
   6.250   1.1964   0.03641   0.02379  -0.0860   0.3678   1.0000
   6.500   1.2169   0.03766   0.02512  -0.0856   0.3642   1.0000
   6.750   1.2334   0.03937   0.02702  -0.0851   0.3600   1.0000
   7.000   1.2520   0.04080   0.02859  -0.0847   0.3568   1.0000
   7.250   1.2721   0.04206   0.02992  -0.0842   0.3543   1.0000
   7.500   1.2938   0.04316   0.03107  -0.0838   0.3521   1.0000
   7.750   1.3160   0.04427   0.03221  -0.0834   0.3503   1.0000
   8.000   1.3128   0.04800   0.03637  -0.0822   0.3465   1.0000
   8.250   1.3106   0.05149   0.04013  -0.0811   0.3430   1.0000
   8.500   1.3129   0.05439   0.04321  -0.0800   0.3398   1.0000
   8.750   1.3229   0.05647   0.04540  -0.0792   0.3374   1.0000
   9.000   1.3402   0.05786   0.04688  -0.0785   0.3355   1.0000
   9.250   1.1314   0.08891   0.07833  -0.0855   0.3225   1.0000
   9.500   1.1369   0.09214   0.08160  -0.0856   0.3205   1.0000
   9.750   1.1559   0.09313   0.08265  -0.0847   0.3189   1.0000
  10.000   1.0881   0.10753   0.09714  -0.0903   0.3117   1.0000
  10.250   1.0874   0.11151   0.10119  -0.0909   0.3083   1.0000
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