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GOE 459 AIRFOIL (goe459-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 459 AIRFOIL (goe459-il)
Reynolds number: 50,000
Max Cl/Cd: 27.75 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe459-il-50000-n5.txt
Download as CSV file: xf-goe459-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 459 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7100   0.09935   0.09148  -0.0323   1.0000   0.0904
 -12.750  -0.7542   0.08714   0.07926  -0.0397   1.0000   0.0897
 -12.500  -0.7981   0.07742   0.06947  -0.0450   1.0000   0.0887
 -12.250  -0.8353   0.07036   0.06226  -0.0475   1.0000   0.0879
 -12.000  -0.8672   0.06510   0.05680  -0.0477   1.0000   0.0880
 -11.750  -0.8944   0.06105   0.05252  -0.0460   1.0000   0.0888
 -11.500  -0.9187   0.05776   0.04896  -0.0429   1.0000   0.0898
 -11.250  -0.9428   0.05495   0.04581  -0.0383   1.0000   0.0912
 -11.000  -0.9290   0.05375   0.04475  -0.0370   1.0000   0.0952
 -10.750  -0.9300   0.05167   0.04251  -0.0344   1.0000   0.0978
 -10.500  -0.9323   0.04934   0.03991  -0.0314   1.0000   0.1004
 -10.250  -0.9347   0.04699   0.03717  -0.0282   1.0000   0.1031
 -10.000  -0.9278   0.04499   0.03497  -0.0259   1.0000   0.1060
  -9.750  -0.9140   0.04337   0.03328  -0.0243   1.0000   0.1088
  -9.500  -0.9008   0.04160   0.03127  -0.0225   1.0000   0.1114
  -9.250  -0.8873   0.03988   0.02929  -0.0207   1.0000   0.1145
  -9.000  -0.8747   0.03826   0.02731  -0.0186   1.0000   0.1185
  -8.750  -0.8559   0.03699   0.02611  -0.0175   1.0000   0.1222
  -8.500  -0.8380   0.03571   0.02471  -0.0161   1.0000   0.1263
  -8.250  -0.8182   0.03437   0.02315  -0.0148   1.0000   0.1307
  -8.000  -0.7981   0.03316   0.02185  -0.0136   1.0000   0.1352
  -7.750  -0.7800   0.03208   0.02075  -0.0121   1.0000   0.1412
  -7.500  -0.7623   0.03104   0.01962  -0.0105   1.0000   0.1494
  -7.250  -0.7465   0.03004   0.01864  -0.0087   1.0000   0.1591
  -7.000  -0.7315   0.02902   0.01768  -0.0067   1.0000   0.1706
  -6.750  -0.7174   0.02803   0.01672  -0.0045   1.0000   0.1848
  -6.500  -0.7043   0.02710   0.01587  -0.0022   1.0000   0.2029
  -6.250  -0.6916   0.02626   0.01510   0.0002   1.0000   0.2248
  -6.000  -0.6796   0.02549   0.01442   0.0028   1.0000   0.2508
  -5.750  -0.6675   0.02476   0.01380   0.0053   1.0000   0.2788
  -5.500  -0.6550   0.02408   0.01320   0.0078   1.0000   0.3086
  -5.250  -0.6423   0.02344   0.01271   0.0104   1.0000   0.3393
  -5.000  -0.6309   0.02285   0.01235   0.0132   1.0000   0.3783
  -4.750  -0.6206   0.02236   0.01214   0.0164   1.0000   0.4259
  -4.500  -0.6097   0.02198   0.01198   0.0196   1.0000   0.4744
  -4.250  -0.5969   0.02167   0.01181   0.0227   1.0000   0.5187
  -4.000  -0.5816   0.02145   0.01174   0.0253   1.0000   0.5575
  -3.750  -0.5650   0.02130   0.01167   0.0278   1.0000   0.5931
  -3.500  -0.5476   0.02120   0.01159   0.0300   1.0000   0.6251
  -3.250  -0.5302   0.02114   0.01155   0.0323   1.0000   0.6563
  -3.000  -0.5121   0.02113   0.01156   0.0344   1.0000   0.6864
  -2.750  -0.4929   0.02116   0.01161   0.0364   1.0000   0.7162
  -2.500  -0.4720   0.02127   0.01173   0.0381   1.0000   0.7464
  -2.250  -0.4489   0.02145   0.01193   0.0394   1.0000   0.7768
  -2.000  -0.4240   0.02168   0.01214   0.0402   1.0000   0.8060
  -1.750  -0.3886   0.02203   0.01245   0.0390   0.9987   0.8311
  -1.500  -0.3389   0.02244   0.01277   0.0347   0.9911   0.8534
  -1.250  -0.2839   0.02290   0.01313   0.0294   0.9843   0.8715
  -1.000  -0.2293   0.02328   0.01343   0.0241   0.9769   0.8884
  -0.750  -0.1682   0.02373   0.01381   0.0177   0.9707   0.9049
  -0.500  -0.1088   0.02406   0.01409   0.0115   0.9632   0.9205
  -0.250  -0.0545   0.02421   0.01421   0.0058   0.9539   0.9338
   0.000   0.0000   0.02426   0.01424   0.0000   0.9446   0.9446
   0.250   0.0545   0.02421   0.01421  -0.0058   0.9338   0.9539
   0.500   0.1087   0.02407   0.01409  -0.0115   0.9205   0.9632
   0.750   0.1681   0.02373   0.01381  -0.0177   0.9050   0.9708
   1.000   0.2292   0.02328   0.01343  -0.0241   0.8884   0.9769
   1.250   0.2840   0.02289   0.01312  -0.0294   0.8715   0.9844
   1.500   0.3389   0.02243   0.01276  -0.0347   0.8534   0.9911
   1.750   0.3887   0.02203   0.01245  -0.0390   0.8312   0.9988
   2.000   0.4238   0.02168   0.01215  -0.0402   0.8061   1.0000
   2.250   0.4488   0.02146   0.01193  -0.0394   0.7771   1.0000
   2.500   0.4719   0.02128   0.01174  -0.0381   0.7470   1.0000
   2.750   0.4928   0.02116   0.01162  -0.0364   0.7165   1.0000
   3.000   0.5121   0.02113   0.01156  -0.0344   0.6867   1.0000
   3.250   0.5302   0.02114   0.01155  -0.0323   0.6565   1.0000
   3.500   0.5476   0.02120   0.01159  -0.0300   0.6255   1.0000
   3.750   0.5650   0.02130   0.01167  -0.0278   0.5932   1.0000
   4.000   0.5815   0.02145   0.01173  -0.0253   0.5576   1.0000
   4.250   0.5969   0.02167   0.01181  -0.0227   0.5189   1.0000
   4.500   0.6095   0.02197   0.01195  -0.0196   0.4742   1.0000
   4.750   0.6206   0.02236   0.01214  -0.0164   0.4259   1.0000
   5.000   0.6309   0.02285   0.01234  -0.0132   0.3784   1.0000
   5.250   0.6422   0.02343   0.01270  -0.0104   0.3392   1.0000
   5.500   0.6550   0.02407   0.01320  -0.0078   0.3087   1.0000
   5.750   0.6675   0.02476   0.01379  -0.0053   0.2789   1.0000
   6.000   0.6796   0.02549   0.01441  -0.0028   0.2507   1.0000
   6.250   0.6916   0.02625   0.01509  -0.0002   0.2248   1.0000
   6.500   0.7043   0.02710   0.01586   0.0022   0.2030   1.0000
   6.750   0.7174   0.02803   0.01672   0.0045   0.1849   1.0000
   7.000   0.7315   0.02902   0.01767   0.0067   0.1706   1.0000
   7.250   0.7466   0.03004   0.01863   0.0087   0.1593   1.0000
   7.500   0.7625   0.03103   0.01962   0.0105   0.1496   1.0000
   7.750   0.7801   0.03208   0.02075   0.0121   0.1413   1.0000
   8.000   0.7982   0.03316   0.02185   0.0136   0.1353   1.0000
   8.250   0.8184   0.03437   0.02315   0.0148   0.1308   1.0000
   8.500   0.8381   0.03570   0.02470   0.0160   0.1264   1.0000
   8.750   0.8561   0.03700   0.02612   0.0174   0.1223   1.0000
   9.000   0.8748   0.03826   0.02731   0.0186   0.1184   1.0000
   9.250   0.8876   0.03987   0.02929   0.0206   0.1146   1.0000
   9.500   0.9010   0.04160   0.03127   0.0225   0.1114   1.0000
   9.750   0.9141   0.04337   0.03327   0.0243   0.1088   1.0000
  10.000   0.9279   0.04499   0.03497   0.0259   0.1060   1.0000
  10.250   0.9351   0.04699   0.03717   0.0281   0.1032   1.0000
  10.500   0.9326   0.04934   0.03991   0.0313   0.1004   1.0000
  10.750   0.9303   0.05170   0.04254   0.0343   0.0979   1.0000
  11.000   0.9295   0.05373   0.04474   0.0370   0.0951   1.0000
  11.250   0.9435   0.05498   0.04584   0.0382   0.0913   1.0000
  11.500   0.9194   0.05778   0.04898   0.0428   0.0899   1.0000
  11.750   0.8943   0.06109   0.05256   0.0460   0.0887   1.0000
  12.000   0.8674   0.06512   0.05683   0.0476   0.0879   1.0000
  12.250   0.8360   0.07035   0.06224   0.0474   0.0878   1.0000
  12.500   0.7979   0.07754   0.06959   0.0448   0.0886   1.0000
  12.750   0.7552   0.08715   0.07928   0.0395   0.0897   1.0000
  13.000   0.7096   0.09965   0.09178   0.0320   0.0903   1.0000
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