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GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 92 AIRFOIL (goe92-il)
Reynolds number: 50,000
Max Cl/Cd: 36.95 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe92-il-50000-n5.txt
Download as CSV file: xf-goe92-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 92 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2728   0.11347   0.10744  -0.0305   1.0000   0.0512
  -8.000  -0.2774   0.11234   0.10645  -0.0312   1.0000   0.0514
  -7.750  -0.2803   0.11104   0.10527  -0.0324   1.0000   0.0515
  -7.500  -0.2655   0.10292   0.09719  -0.0274   1.0000   0.0535
  -7.250  -0.2652   0.10015   0.09450  -0.0257   1.0000   0.0549
  -7.000  -0.2685   0.09810   0.09255  -0.0244   1.0000   0.0562
  -6.750  -0.2732   0.09628   0.09085  -0.0232   1.0000   0.0576
  -6.500  -0.2782   0.09455   0.08920  -0.0222   1.0000   0.0591
  -6.250  -0.2824   0.09280   0.08755  -0.0217   1.0000   0.0608
  -6.000  -0.2852   0.09112   0.08595  -0.0221   1.0000   0.0629
  -5.750  -0.2847   0.08992   0.08479  -0.0248   1.0000   0.0650
  -5.500  -0.2567   0.08600   0.08083  -0.0337   0.9924   0.0669
  -5.250  -0.2398   0.08088   0.07576  -0.0329   0.9859   0.0727
  -5.000  -0.1902   0.07742   0.07203  -0.0481   0.9729   0.0809
  -4.750  -0.1722   0.07217   0.06687  -0.0475   0.9658   0.0868
  -4.500  -0.1325   0.06800   0.06255  -0.0563   0.9547   0.0971
  -4.000  -0.0611   0.05984   0.05417  -0.0675   0.9313   0.1277
  -3.750  -0.0232   0.05582   0.05005  -0.0727   0.9192   0.1579
  -2.750   0.1669   0.04060   0.03313  -0.0925   0.8665   0.0899
  -2.500   0.2062   0.03805   0.02997  -0.0940   0.8521   0.0789
  -2.250   0.2373   0.03538   0.02699  -0.0946   0.8365   0.0740
  -2.000   0.2713   0.03322   0.02425  -0.0948   0.8204   0.0687
  -1.750   0.3008   0.03141   0.02212  -0.0948   0.8033   0.0720
  -1.500   0.3315   0.02979   0.02008  -0.0945   0.7860   0.0736
  -1.250   0.3623   0.02828   0.01811  -0.0940   0.7686   0.0728
  -1.000   0.3910   0.02707   0.01653  -0.0933   0.7489   0.0737
  -0.750   0.4195   0.02622   0.01525  -0.0924   0.7290   0.0794
  -0.500   0.4489   0.02526   0.01391  -0.0915   0.7102   0.0803
  -0.250   0.4780   0.02441   0.01274  -0.0907   0.6899   0.0809
   0.000   0.5061   0.02367   0.01173  -0.0899   0.6706   0.0822
   0.250   0.5336   0.02313   0.01090  -0.0890   0.6522   0.0839
   0.500   0.5601   0.02282   0.01030  -0.0883   0.6332   0.0864
   0.750   0.5867   0.02265   0.00986  -0.0876   0.6149   0.0910
   1.000   0.6134   0.02253   0.00956  -0.0871   0.5976   0.1030
   1.250   0.6403   0.02250   0.00936  -0.0867   0.5813   0.1173
   1.500   0.6653   0.02165   0.00941  -0.0866   0.5662   0.4142
   1.750   0.6927   0.02099   0.00931  -0.0858   0.5515   1.0000
   2.000   0.7187   0.02141   0.00938  -0.0853   0.5379   1.0000
   2.250   0.7447   0.02185   0.00955  -0.0849   0.5257   1.0000
   2.500   0.7708   0.02230   0.00975  -0.0845   0.5148   1.0000
   2.750   0.7968   0.02275   0.00999  -0.0842   0.5047   1.0000
   3.000   0.8221   0.02325   0.01038  -0.0839   0.4944   1.0000
   3.250   0.8479   0.02373   0.01072  -0.0837   0.4858   1.0000
   3.500   0.8734   0.02425   0.01114  -0.0834   0.4774   1.0000
   3.750   0.8989   0.02480   0.01165  -0.0832   0.4701   1.0000
   4.000   0.9244   0.02536   0.01218  -0.0830   0.4632   1.0000
   4.250   0.9499   0.02593   0.01271  -0.0828   0.4570   1.0000
   4.500   0.9744   0.02656   0.01341  -0.0825   0.4502   1.0000
   4.750   1.0006   0.02708   0.01387  -0.0823   0.4451   1.0000
   5.000   1.0237   0.02786   0.01479  -0.0820   0.4385   1.0000
   5.250   1.0487   0.02852   0.01551  -0.0818   0.4336   1.0000
   5.500   1.0738   0.02919   0.01627  -0.0815   0.4290   1.0000
   5.750   1.0959   0.03008   0.01735  -0.0811   0.4231   1.0000
   6.000   1.1204   0.03077   0.01812  -0.0808   0.4183   1.0000
   6.250   1.1438   0.03159   0.01912  -0.0805   0.4136   1.0000
   6.500   1.1646   0.03258   0.02036  -0.0799   0.4078   1.0000
   6.750   1.1895   0.03317   0.02102  -0.0796   0.4024   1.0000
   7.000   1.2078   0.03415   0.02226  -0.0787   0.3946   1.0000
   7.250   1.2331   0.03443   0.02264  -0.0781   0.3871   1.0000
   7.500   1.2491   0.03535   0.02385  -0.0768   0.3774   1.0000
   7.750   1.2695   0.03580   0.02444  -0.0757   0.3677   1.0000
   8.000   1.2848   0.03559   0.02427  -0.0736   0.3487   1.0000
   8.250   1.2993   0.03536   0.02401  -0.0714   0.3294   1.0000
   8.500   1.3115   0.03576   0.02455  -0.0693   0.3140   1.0000
   8.750   1.3217   0.03652   0.02562  -0.0672   0.3005   1.0000
   9.000   1.3286   0.03725   0.02652  -0.0648   0.2844   1.0000
   9.250   1.3290   0.03842   0.02795  -0.0621   0.2637   1.0000
   9.500   1.3307   0.03974   0.02953  -0.0596   0.2466   1.0000
   9.750   1.3308   0.04133   0.03132  -0.0573   0.2269   1.0000
  10.000   1.3285   0.04333   0.03341  -0.0554   0.1964   1.0000
  10.250   1.3209   0.04583   0.03566  -0.0536   0.1638   1.0000
  10.750   1.2977   0.05335   0.04302  -0.0521   0.1269   1.0000
  11.000   1.2832   0.05814   0.04786  -0.0524   0.1112   1.0000
  11.500   1.2500   0.06942   0.05927  -0.0549   0.0560   1.0000
  12.000   1.2120   0.08216   0.07203  -0.0585   0.0447   1.0000
  12.250   1.1969   0.08809   0.07805  -0.0600   0.0420   1.0000
  12.500   1.1834   0.09386   0.08392  -0.0616   0.0395   1.0000
  12.750   1.1714   0.09948   0.08964  -0.0631   0.0376   1.0000
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