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GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 392 AIRFOIL (goe392-il)
Reynolds number: 100,000
Max Cl/Cd: 59.27 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe392-il-100000.txt
Download as CSV file: xf-goe392-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 392 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3569   0.09626   0.09232  -0.0298   1.0000   0.0664
  -7.000  -0.3769   0.09567   0.09185  -0.0263   1.0000   0.0667
  -6.750  -0.3955   0.09481   0.09109  -0.0238   1.0000   0.0673
  -6.500  -0.4098   0.09341   0.08977  -0.0234   1.0000   0.0681
  -6.250  -0.4105   0.09042   0.08682  -0.0330   0.9973   0.0697
  -6.000  -0.3923   0.08506   0.08147  -0.0341   0.9922   0.0723
  -5.750  -0.3662   0.08096   0.07728  -0.0384   0.9854   0.0790
  -5.500  -0.3349   0.07429   0.07051  -0.0519   0.9755   0.0855
  -5.250  -0.2968   0.06832   0.06425  -0.0659   0.9663   0.0977
  -5.000  -0.2646   0.06396   0.05967  -0.0729   0.9588   0.1113
  -4.750  -0.2485   0.06059   0.05647  -0.0715   0.9516   0.1267
  -4.500  -0.2163   0.05708   0.05284  -0.0763   0.9452   0.1537
  -4.250  -0.1974   0.05497   0.05080  -0.0749   0.9366   0.1731
  -4.000  -0.1636   0.05186   0.04763  -0.0784   0.9313   0.2118
  -3.750  -0.1416   0.04968   0.04539  -0.0791   0.9216   0.2507
  -3.250  -0.0163   0.03356   0.02614  -0.0980   0.9102   0.0835
  -3.000   0.0272   0.02974   0.02174  -0.1001   0.9061   0.0689
  -2.750   0.0606   0.02833   0.01981  -0.1006   0.8977   0.0702
  -2.500   0.1030   0.02587   0.01709  -0.1027   0.8931   0.0691
  -2.250   0.1368   0.02443   0.01546  -0.1032   0.8855   0.0696
  -2.000   0.1768   0.02275   0.01388  -0.1051   0.8802   0.0766
  -1.750   0.2103   0.02180   0.01284  -0.1058   0.8726   0.0878
  -1.500   0.2518   0.02064   0.01167  -0.1080   0.8670   0.1172
  -1.250   0.2903   0.01805   0.01134  -0.1093   0.8643   0.6828
  -1.000   0.3464   0.01734   0.01078  -0.1143   0.8567   1.0000
  -0.750   0.3934   0.01700   0.01004  -0.1176   0.8515   1.0000
  -0.500   0.4239   0.01702   0.00981  -0.1181   0.8412   1.0000
  -0.250   0.4610   0.01688   0.00944  -0.1196   0.8329   1.0000
   0.000   0.4997   0.01666   0.00901  -0.1214   0.8249   1.0000
   0.250   0.5288   0.01670   0.00889  -0.1215   0.8139   1.0000
   0.500   0.5601   0.01670   0.00875  -0.1219   0.8039   1.0000
   0.750   0.5980   0.01653   0.00843  -0.1234   0.7961   1.0000
   1.000   0.6230   0.01672   0.00854  -0.1228   0.7845   1.0000
   1.250   0.6489   0.01690   0.00865  -0.1224   0.7735   1.0000
   1.500   0.6769   0.01704   0.00872  -0.1223   0.7635   1.0000
   1.750   0.7097   0.01704   0.00863  -0.1229   0.7550   1.0000
   2.000   0.7328   0.01730   0.00888  -0.1220   0.7435   1.0000
   2.250   0.7572   0.01755   0.00916  -0.1214   0.7327   1.0000
   2.500   0.7839   0.01774   0.00933  -0.1211   0.7228   1.0000
   2.750   0.8146   0.01781   0.00937  -0.1213   0.7141   1.0000
   3.000   0.8371   0.01811   0.00973  -0.1204   0.7028   1.0000
   3.250   0.8611   0.01839   0.01012  -0.1196   0.6920   1.0000
   3.500   0.8875   0.01861   0.01039  -0.1192   0.6822   1.0000
   3.750   0.9145   0.01811   0.00987  -0.1180   0.6625   1.0000
   4.000   0.9381   0.01742   0.00909  -0.1157   0.6354   1.0000
   4.250   0.9591   0.01688   0.00843  -0.1131   0.6048   1.0000
   4.500   0.9746   0.01671   0.00830  -0.1099   0.5718   1.0000
   4.750   0.9898   0.01670   0.00819  -0.1068   0.5342   1.0000
   5.000   0.9986   0.01694   0.00821  -0.1026   0.4760   1.0000
   5.250   1.0068   0.01755   0.00846  -0.0985   0.4020   1.0000
   5.500   1.0097   0.01881   0.00906  -0.0941   0.3018   1.0000
   5.750   0.9928   0.02202   0.01083  -0.0876   0.0689   1.0000
   6.000   1.0049   0.02316   0.01195  -0.0848   0.0542   1.0000
   6.250   1.0167   0.02421   0.01316  -0.0820   0.0497   1.0000
   6.500   1.0248   0.02537   0.01450  -0.0787   0.0464   1.0000
   6.750   1.0322   0.02652   0.01591  -0.0755   0.0437   1.0000
   7.000   1.0365   0.02783   0.01743  -0.0719   0.0426   1.0000
   7.250   1.0384   0.02929   0.01907  -0.0682   0.0423   1.0000
   7.500   1.0391   0.03087   0.02080  -0.0647   0.0424   1.0000
   7.750   1.0403   0.03255   0.02260  -0.0614   0.0426   1.0000
   8.000   1.0454   0.03428   0.02438  -0.0585   0.0431   1.0000
   8.250   1.0671   0.03590   0.02593  -0.0568   0.0443   1.0000
   8.500   1.1778   0.03961   0.02941  -0.0658   0.0488   1.0000
   8.750   1.2719   0.04622   0.03633  -0.0737   0.0587   1.0000
   9.250   1.3841   0.05182   0.04396  -0.0713   0.1324   1.0000
   9.500   1.3954   0.05467   0.04863  -0.0650   0.1872   1.0000
   9.750   1.3676   0.05966   0.05452  -0.0592   0.2049   1.0000
  10.000   1.3389   0.06618   0.06157  -0.0552   0.2215   1.0000
  10.250   1.3034   0.06952   0.06514  -0.0501   0.2199   1.0000
  10.500   1.2696   0.07377   0.06953  -0.0461   0.2208   1.0000
  10.750   1.2370   0.07898   0.07485  -0.0440   0.2220   1.0000
  11.000   1.2056   0.08505   0.08099  -0.0436   0.2229   1.0000
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