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GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 492 AIRFOIL (goe492-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.59 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe492-il-1000000.txt
Download as CSV file: xf-goe492-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 492 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4035   0.08872   0.08715  -0.0302   1.0000   0.0098
  -8.000  -0.4081   0.08623   0.08469  -0.0293   1.0000   0.0098
  -7.750  -0.4199   0.08445   0.08295  -0.0267   1.0000   0.0098
  -7.500  -0.4033   0.07942   0.07793  -0.0333   0.9972   0.0098
  -7.250  -0.3797   0.07349   0.07199  -0.0424   0.9941   0.0098
  -7.000  -0.3579   0.06751   0.06599  -0.0512   0.9899   0.0099
  -6.750  -0.3317   0.02208   0.01941  -0.0961   0.9775   0.0062
  -6.500  -0.3034   0.01767   0.01444  -0.0988   0.9746   0.0068
  -6.250  -0.2714   0.01676   0.01335  -0.1004   0.9727   0.0075
  -6.000  -0.2406   0.01481   0.01108  -0.1018   0.9705   0.0080
  -5.750  -0.2126   0.01301   0.00895  -0.1023   0.9668   0.0084
  -5.500  -0.1859   0.01162   0.00731  -0.1023   0.9622   0.0088
  -5.250  -0.1567   0.01089   0.00643  -0.1027   0.9588   0.0094
  -5.000  -0.1260   0.01049   0.00593  -0.1034   0.9560   0.0099
  -4.750  -0.1031   0.00865   0.00375  -0.1025   0.9495   0.0121
  -4.500  -0.0749   0.00830   0.00334  -0.1026   0.9451   0.0138
  -4.250  -0.0467   0.00800   0.00297  -0.1026   0.9409   0.0155
  -4.000  -0.0205   0.00755   0.00245  -0.1023   0.9351   0.0200
  -3.750   0.0079   0.00756   0.00249  -0.1023   0.9304   0.0247
  -3.500   0.0349   0.00731   0.00221  -0.1022   0.9250   0.0316
  -3.250   0.0622   0.00725   0.00213  -0.1020   0.9195   0.0349
  -3.000   0.0902   0.00728   0.00214  -0.1020   0.9144   0.0364
  -2.750   0.1163   0.00691   0.00170  -0.1017   0.9080   0.0405
  -2.250   0.1703   0.00665   0.00136  -0.1012   0.8945   0.0487
  -2.000   0.1976   0.00652   0.00117  -0.1010   0.8878   0.0518
  -1.750   0.2241   0.00636   0.00100  -0.1007   0.8790   0.0585
  -1.500   0.2507   0.00617   0.00086  -0.1004   0.8705   0.0839
  -1.250   0.2763   0.00571   0.00080  -0.1002   0.8625   0.2281
  -1.000   0.3034   0.00565   0.00079  -0.1000   0.8545   0.2557
  -0.750   0.3305   0.00563   0.00076  -0.0998   0.8462   0.2709
  -0.500   0.3574   0.00561   0.00074  -0.0996   0.8360   0.2846
  -0.250   0.3842   0.00559   0.00073  -0.0993   0.8244   0.2977
   0.000   0.4111   0.00558   0.00071  -0.0991   0.8123   0.3083
   0.250   0.4376   0.00556   0.00069  -0.0988   0.7983   0.3202
   0.750   0.4887   0.00521   0.00071  -0.0980   0.7643   0.4897
   1.000   0.5085   0.00451   0.00084  -0.0964   0.7446   0.8046
   1.250   0.5478   0.00426   0.00087  -0.0989   0.7177   1.0000
   1.500   0.5718   0.00447   0.00092  -0.0980   0.6845   1.0000
   1.750   0.5961   0.00467   0.00100  -0.0973   0.6535   1.0000
   2.000   0.6201   0.00492   0.00109  -0.0964   0.6192   1.0000
   2.250   0.6442   0.00518   0.00122  -0.0957   0.5812   1.0000
   2.500   0.6677   0.00549   0.00133  -0.0948   0.5300   1.0000
   2.750   0.6872   0.00618   0.00155  -0.0933   0.4197   1.0000
   3.000   0.7006   0.00764   0.00207  -0.0910   0.2087   1.0000
   3.250   0.7178   0.00883   0.00259  -0.0894   0.0486   1.0000
   3.500   0.7413   0.00934   0.00298  -0.0885   0.0185   1.0000
   3.750   0.7661   0.00969   0.00340  -0.0878   0.0149   1.0000
   4.000   0.7908   0.01003   0.00378  -0.0872   0.0133   1.0000
   4.250   0.8151   0.01042   0.00421  -0.0865   0.0120   1.0000
   4.500   0.8379   0.01099   0.00484  -0.0855   0.0105   1.0000
   4.750   0.8519   0.01273   0.00677  -0.0826   0.0093   1.0000
   5.000   0.8760   0.01314   0.00721  -0.0819   0.0089   1.0000
   5.250   0.8996   0.01361   0.00775  -0.0811   0.0083   1.0000
   5.500   0.9211   0.01451   0.00871  -0.0799   0.0080   1.0000
   5.750   0.9431   0.01549   0.00976  -0.0787   0.0076   1.0000
   6.000   0.9659   0.01640   0.01074  -0.0778   0.0070   1.0000
   6.250   0.9892   0.01704   0.01142  -0.0771   0.0064   1.0000
   6.500   1.0117   0.01798   0.01242  -0.0762   0.0059   1.0000
   6.750   1.0332   0.02010   0.01472  -0.0750   0.0056   1.0000
   7.000   1.0041   0.02466   0.02079  -0.0650   0.0091   1.0000
   7.250   1.0149   0.02815   0.02454  -0.0627   0.0091   1.0000
   7.500   1.0235   0.03182   0.02849  -0.0601   0.0091   1.0000
   7.750   1.0329   0.03495   0.03185  -0.0577   0.0090   1.0000
   8.000   1.0605   0.03481   0.03181  -0.0566   0.0076   1.0000
   8.250   1.0684   0.03825   0.03544  -0.0543   0.0069   1.0000
   8.500   1.0706   0.04227   0.03966  -0.0517   0.0066   1.0000
   8.750   1.0689   0.04640   0.04398  -0.0490   0.0064   1.0000
   9.000   1.0637   0.05034   0.04807  -0.0462   0.0063   1.0000
   9.250   1.0528   0.05413   0.05200  -0.0430   0.0062   1.0000
   9.500   1.0319   0.05746   0.05546  -0.0387   0.0062   1.0000
   9.750   1.0083   0.06129   0.05941  -0.0357   0.0062   1.0000
  10.000   0.9811   0.06631   0.06456  -0.0343   0.0062   1.0000
  10.250   0.9511   0.07257   0.07095  -0.0347   0.0063   1.0000
  10.500   0.9186   0.08043   0.07893  -0.0374   0.0065   1.0000
  10.750   0.8852   0.09010   0.08872  -0.0427   0.0068   1.0000
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