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GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il)
Reynolds number: 500,000
Max Cl/Cd: 100.89 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe277-il-500000.txt
Download as CSV file: xf-goe277-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 277 (DAIMLER VIII) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3442   0.08663   0.08450  -0.0245   1.0000   0.0201
  -7.500  -0.3500   0.08465   0.08257  -0.0232   1.0000   0.0204
  -7.250  -0.3552   0.08253   0.08050  -0.0225   1.0000   0.0207
  -7.000  -0.3613   0.08043   0.07844  -0.0217   1.0000   0.0211
  -6.750  -0.3454   0.07629   0.07429  -0.0272   0.9979   0.0221
  -6.500  -0.2927   0.06768   0.06554  -0.0478   0.9928   0.0237
  -6.250  -0.2561   0.06122   0.05896  -0.0573   0.9884   0.0238
  -5.000  -0.0912   0.03542   0.03233  -0.0844   0.9665   0.0310
  -4.750  -0.0649   0.03323   0.03010  -0.0860   0.9588   0.0317
  -4.500  -0.0392   0.03139   0.02817  -0.0869   0.9501   0.0328
  -4.250  -0.0114   0.02924   0.02587  -0.0878   0.9418   0.0346
  -4.000   0.0216   0.02880   0.02500  -0.0872   0.9301   0.0389
  -3.750   0.0434   0.02311   0.01896  -0.0882   0.9182   0.0407
  -3.500   0.0677   0.02174   0.01752  -0.0880   0.9047   0.0419
  -3.250   0.0930   0.02056   0.01620  -0.0877   0.8898   0.0437
  -3.000   0.1197   0.01958   0.01499  -0.0873   0.8733   0.0475
  -2.750   0.1471   0.01782   0.01276  -0.0869   0.8549   0.0525
  -2.500   0.1727   0.01667   0.01154  -0.0867   0.8324   0.0544
  -2.250  -0.0448   0.09178   0.08950  -0.0324   0.9262   0.0393
  -1.500   0.2824   0.01244   0.00611  -0.0844   0.7377   0.0467
  -1.250   0.3100   0.01152   0.00495  -0.0840   0.7199   0.0444
  -1.000   0.3375   0.01097   0.00426  -0.0837   0.7023   0.0439
  -0.750   0.3649   0.01056   0.00374  -0.0834   0.6844   0.0439
  -0.500   0.3922   0.01026   0.00336  -0.0832   0.6653   0.0445
  -0.250   0.4194   0.01006   0.00306  -0.0829   0.6446   0.0458
   0.000   0.4468   0.00983   0.00274  -0.0827   0.6214   0.0463
   0.250   0.4739   0.00969   0.00249  -0.0825   0.5974   0.0474
   0.500   0.5011   0.00962   0.00230  -0.0822   0.5729   0.0486
   0.750   0.5283   0.00961   0.00218  -0.0821   0.5499   0.0499
   1.000   0.5554   0.00959   0.00204  -0.0819   0.5281   0.0522
   1.250   0.5827   0.00960   0.00197  -0.0817   0.5074   0.0581
   1.500   0.6100   0.00964   0.00195  -0.0816   0.4862   0.0751
   1.750   0.6323   0.00768   0.00211  -0.0809   0.4669   1.0000
   2.000   0.6595   0.00787   0.00216  -0.0808   0.4465   1.0000
   2.250   0.6865   0.00807   0.00224  -0.0806   0.4278   1.0000
   2.500   0.7135   0.00828   0.00233  -0.0805   0.4118   1.0000
   2.750   0.7405   0.00849   0.00244  -0.0803   0.3982   1.0000
   3.000   0.7675   0.00870   0.00256  -0.0802   0.3859   1.0000
   3.250   0.7944   0.00892   0.00269  -0.0800   0.3757   1.0000
   3.500   0.8215   0.00911   0.00285  -0.0799   0.3675   1.0000
   3.750   0.8485   0.00932   0.00301  -0.0798   0.3610   1.0000
   4.000   0.8755   0.00950   0.00317  -0.0797   0.3541   1.0000
   4.250   0.9022   0.00973   0.00334  -0.0795   0.3470   1.0000
   4.500   0.9294   0.00990   0.00352  -0.0794   0.3408   1.0000
   4.750   0.9559   0.01013   0.00373  -0.0793   0.3359   1.0000
   5.000   0.9828   0.01033   0.00393  -0.0791   0.3313   1.0000
   5.250   1.0098   0.01050   0.00414  -0.0790   0.3260   1.0000
   5.500   1.0359   0.01077   0.00436  -0.0788   0.3188   1.0000
   5.750   1.0629   0.01088   0.00452  -0.0787   0.3105   1.0000
   6.000   1.0891   0.01111   0.00474  -0.0785   0.3029   1.0000
   6.250   1.1158   0.01126   0.00493  -0.0784   0.2941   1.0000
   6.500   1.1421   0.01145   0.00513  -0.0782   0.2854   1.0000
   6.750   1.1681   0.01167   0.00535  -0.0780   0.2762   1.0000
   7.000   1.1945   0.01184   0.00557  -0.0779   0.2648   1.0000
   7.250   1.2199   0.01210   0.00579  -0.0776   0.2466   1.0000
   7.500   1.2442   0.01251   0.00607  -0.0772   0.2118   1.0000
   7.750   1.2601   0.01391   0.00694  -0.0758   0.1280   1.0000
   8.000   1.2763   0.01528   0.00797  -0.0744   0.0780   1.0000
   8.250   1.2898   0.01691   0.00923  -0.0725   0.0255   1.0000
   8.500   1.3095   0.01775   0.01011  -0.0713   0.0209   1.0000
   8.750   1.3301   0.01846   0.01092  -0.0703   0.0192   1.0000
   9.000   1.3496   0.01922   0.01178  -0.0691   0.0180   1.0000
   9.250   1.3672   0.02012   0.01278  -0.0677   0.0169   1.0000
   9.500   1.3810   0.02130   0.01405  -0.0658   0.0160   1.0000
   9.750   1.3892   0.02283   0.01572  -0.0632   0.0151   1.0000
  10.000   1.4043   0.02367   0.01665  -0.0615   0.0146   1.0000
  10.250   1.4148   0.02471   0.01778  -0.0591   0.0141   1.0000
  10.500   1.4205   0.02589   0.01906  -0.0561   0.0137   1.0000
  10.750   1.4248   0.02724   0.02051  -0.0533   0.0133   1.0000
  11.000   1.4279   0.02877   0.02215  -0.0506   0.0130   1.0000
  11.250   1.4300   0.03049   0.02397  -0.0482   0.0126   1.0000
  11.500   1.4307   0.03247   0.02604  -0.0461   0.0124   1.0000
  11.750   1.4297   0.03477   0.02842  -0.0442   0.0121   1.0000
  12.000   1.4273   0.03738   0.03113  -0.0427   0.0119   1.0000
  12.250   1.4233   0.04035   0.03419  -0.0413   0.0117   1.0000
  12.500   1.4191   0.04348   0.03740  -0.0399   0.0115   1.0000
  12.750   1.4162   0.04661   0.04060  -0.0380   0.0113   1.0000
  13.000   1.4192   0.04911   0.04326  -0.0378   0.0112   1.0000
  13.250   1.4212   0.05182   0.04611  -0.0378   0.0110   1.0000
  13.500   1.4222   0.05472   0.04915  -0.0378   0.0108   1.0000
  13.750   1.4220   0.05781   0.05238  -0.0379   0.0105   1.0000
  14.000   1.4208   0.06105   0.05575  -0.0379   0.0104   1.0000
  14.250   1.4187   0.06448   0.05932  -0.0381   0.0102   1.0000
  14.500   1.4157   0.06808   0.06305  -0.0383   0.0101   1.0000
  14.750   1.4117   0.07189   0.06700  -0.0386   0.0100   1.0000
  15.000   1.4067   0.07596   0.07122  -0.0393   0.0099   1.0000
  15.250   1.4007   0.08029   0.07570  -0.0402   0.0098   1.0000
  15.500   1.3932   0.08494   0.08050  -0.0414   0.0098   1.0000
  15.750   1.3849   0.08987   0.08558  -0.0429   0.0097   1.0000
  16.000   1.3751   0.09519   0.09108  -0.0448   0.0097   1.0000
  16.250   1.3641   0.10086   0.09691  -0.0470   0.0097   1.0000
  16.500   1.3517   0.10695   0.10317  -0.0496   0.0097   1.0000
  16.750   1.3386   0.11341   0.10980  -0.0527   0.0097   1.0000
  17.000   1.3245   0.12028   0.11684  -0.0562   0.0098   1.0000
  17.250   1.3095   0.12754   0.12427  -0.0601   0.0098   1.0000
  17.500   1.2941   0.13516   0.13206  -0.0644   0.0099   1.0000
  17.750   1.2782   0.14320   0.14026  -0.0692   0.0100   1.0000
  18.000   1.2618   0.15173   0.14895  -0.0745   0.0101   1.0000
  18.250   1.2449   0.16077   0.15815  -0.0803   0.0103   1.0000
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