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GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 379 AIRFOIL (goe379-il)
Reynolds number: 500,000
Max Cl/Cd: 103.82 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe379-il-500000-n5.txt
Download as CSV file: xf-goe379-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 379 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2841   0.10032   0.09819  -0.0282   1.0000   0.0059
  -8.250  -0.2811   0.09728   0.09518  -0.0277   1.0000   0.0060
  -8.000  -0.2792   0.09484   0.09277  -0.0273   1.0000   0.0061
  -7.750  -0.2670   0.09152   0.08946  -0.0300   0.9919   0.0062
  -7.500  -0.2517   0.08791   0.08586  -0.0340   0.9817   0.0062
  -7.250  -0.2340   0.08437   0.08231  -0.0383   0.9714   0.0065
  -7.000  -0.2105   0.08021   0.07814  -0.0448   0.9602   0.0066
  -6.750  -0.1827   0.07596   0.07386  -0.0521   0.9488   0.0071
  -6.500  -0.1534   0.07166   0.06952  -0.0597   0.9348   0.0071
  -6.250  -0.1265   0.06762   0.06541  -0.0662   0.9166   0.0074
  -6.000  -0.1052   0.06415   0.06184  -0.0707   0.8975   0.0076
  -5.750  -0.0870   0.06095   0.05855  -0.0739   0.8787   0.0079
  -5.500  -0.0671   0.05788   0.05537  -0.0770   0.8621   0.0086
  -4.500   0.0154   0.04306   0.04005  -0.0870   0.8060   0.0054
  -4.250   0.0390   0.03952   0.03634  -0.0887   0.7912   0.0053
  -4.000   0.0635   0.03596   0.03259  -0.0900   0.7762   0.0054
  -3.750   0.0898   0.03204   0.02843  -0.0908   0.7621   0.0058
  -3.500   0.1137   0.02850   0.02465  -0.0914   0.7492   0.0063
  -3.250   0.1379   0.02684   0.02281  -0.0914   0.7369   0.0070
  -3.000   0.1618   0.01991   0.01528  -0.0900   0.7282   0.0064
  -2.750   0.1827   0.01360   0.00805  -0.0878   0.7190   0.0062
  -2.500   0.2074   0.01215   0.00621  -0.0870   0.7071   0.0065
  -2.250   0.2328   0.01128   0.00505  -0.0863   0.6949   0.0069
  -2.000   0.2584   0.01064   0.00419  -0.0856   0.6826   0.0078
  -1.750   0.2841   0.01023   0.00360  -0.0850   0.6691   0.0090
  -1.500   0.3092   0.00967   0.00284  -0.0842   0.6551   0.0107
  -1.250   0.3344   0.00928   0.00226  -0.0834   0.6402   0.0131
  -1.000   0.3599   0.00909   0.00196  -0.0828   0.6255   0.0185
  -0.750   0.3854   0.00898   0.00185  -0.0823   0.6112   0.0354
  -0.500   0.4114   0.00902   0.00180  -0.0819   0.5966   0.0455
  -0.250   0.4371   0.00904   0.00173  -0.0814   0.5816   0.0517
   0.000   0.4629   0.00907   0.00169  -0.0810   0.5674   0.0583
   0.250   0.4884   0.00907   0.00158  -0.0805   0.5537   0.0611
   0.500   0.5140   0.00906   0.00150  -0.0800   0.5418   0.0648
   0.750   0.5398   0.00907   0.00147  -0.0796   0.5304   0.0706
   1.000   0.5656   0.00910   0.00145  -0.0792   0.5188   0.0786
   1.250   0.5911   0.00914   0.00145  -0.0788   0.5061   0.0892
   1.500   0.6165   0.00918   0.00147  -0.0783   0.4923   0.1048
   1.750   0.6417   0.00922   0.00151  -0.0778   0.4778   0.1320
   2.000   0.6664   0.00916   0.00160  -0.0773   0.4653   0.2192
   2.500   0.7774   0.00796   0.00190  -0.0908   0.4354   1.0000
   2.750   0.8019   0.00812   0.00198  -0.0902   0.4223   1.0000
   3.000   0.8261   0.00830   0.00208  -0.0895   0.4064   1.0000
   3.250   0.8504   0.00849   0.00220  -0.0889   0.3926   1.0000
   3.500   0.8746   0.00867   0.00234  -0.0882   0.3809   1.0000
   3.750   0.8987   0.00886   0.00248  -0.0876   0.3693   1.0000
   4.000   0.9230   0.00905   0.00264  -0.0869   0.3589   1.0000
   4.250   0.9473   0.00922   0.00282  -0.0863   0.3508   1.0000
   4.500   0.9714   0.00941   0.00301  -0.0857   0.3431   1.0000
   4.750   0.9956   0.00959   0.00320  -0.0850   0.3350   1.0000
   5.000   1.0181   0.00991   0.00343  -0.0842   0.3153   1.0000
   5.250   1.0401   0.01026   0.00371  -0.0832   0.2896   1.0000
   5.500   1.0609   0.01071   0.00401  -0.0821   0.2551   1.0000
   5.750   1.0737   0.01189   0.00464  -0.0798   0.1626   1.0000
   6.000   1.0767   0.01402   0.00599  -0.0760   0.0174   1.0000
   6.250   1.0972   0.01453   0.00656  -0.0747   0.0100   1.0000
   6.500   1.1182   0.01495   0.00708  -0.0735   0.0081   1.0000
   6.750   1.1372   0.01554   0.00778  -0.0720   0.0067   1.0000
   7.000   1.1557   0.01618   0.00853  -0.0705   0.0057   1.0000
   7.250   1.1747   0.01672   0.00913  -0.0691   0.0048   1.0000
   7.500   1.1913   0.01744   0.00992  -0.0673   0.0043   1.0000
   7.750   1.2035   0.01849   0.01109  -0.0647   0.0038   1.0000
   8.000   1.2165   0.01939   0.01210  -0.0624   0.0037   1.0000
   8.250   1.2264   0.02045   0.01332  -0.0595   0.0035   1.0000
   8.500   1.2338   0.02155   0.01454  -0.0563   0.0033   1.0000
   8.750   1.2367   0.02268   0.01578  -0.0524   0.0033   1.0000
   9.000   1.2390   0.02394   0.01714  -0.0485   0.0031   1.0000
   9.250   1.2439   0.02514   0.01843  -0.0455   0.0029   1.0000
   9.500   1.2469   0.02662   0.02001  -0.0424   0.0028   1.0000
   9.750   1.2567   0.02753   0.02096  -0.0408   0.0025   1.0000
  10.000   1.2579   0.02935   0.02289  -0.0381   0.0023   1.0000
  10.250   1.2609   0.03125   0.02494  -0.0357   0.0022   1.0000
  10.500   1.2647   0.03324   0.02706  -0.0335   0.0022   1.0000
  10.750   1.2694   0.03566   0.02967  -0.0311   0.0019   1.0000
  11.000   1.2756   0.03804   0.03222  -0.0291   0.0019   1.0000
  11.250   1.2818   0.04063   0.03500  -0.0271   0.0018   1.0000
  11.500   1.2859   0.04354   0.03813  -0.0252   0.0017   1.0000
  11.750   1.2866   0.04664   0.04146  -0.0234   0.0017   1.0000
  12.000   1.2837   0.05019   0.04524  -0.0218   0.0017   1.0000
  12.250   1.2797   0.05347   0.04872  -0.0206   0.0017   1.0000
  12.500   1.2717   0.05737   0.05284  -0.0196   0.0018   1.0000
  12.750   1.2612   0.06154   0.05721  -0.0192   0.0018   1.0000
  13.000   1.2479   0.06622   0.06211  -0.0192   0.0017   1.0000
  13.250   1.2351   0.07091   0.06699  -0.0199   0.0017   1.0000
  13.500   1.2213   0.07595   0.07221  -0.0211   0.0018   1.0000
  13.750   1.2043   0.08181   0.07825  -0.0229   0.0018   1.0000
  14.000   1.1890   0.08768   0.08429  -0.0252   0.0018   1.0000
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