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GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 264 AIRFOIL (goe264-il)
Reynolds number: 50,000
Max Cl/Cd: 41.85 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe264-il-50000-n5.txt
Download as CSV file: xf-goe264-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 264 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2960   0.10013   0.09373  -0.0246   1.0000   0.0774
  -7.000  -0.2952   0.09842   0.09213  -0.0260   1.0000   0.0798
  -6.750  -0.2938   0.09743   0.09124  -0.0294   1.0000   0.0812
  -6.500  -0.2882   0.09635   0.09020  -0.0339   1.0000   0.0818
  -6.250  -0.2861   0.09121   0.08514  -0.0296   1.0000   0.0835
  -6.000  -0.2826   0.08804   0.08202  -0.0271   1.0000   0.0877
  -5.750  -0.2764   0.08604   0.08006  -0.0289   1.0000   0.0928
  -5.500  -0.2553   0.08582   0.07975  -0.0391   1.0000   0.0958
  -5.250  -0.2559   0.08108   0.07514  -0.0351   1.0000   0.0971
  -5.000  -0.2523   0.07777   0.07189  -0.0328   1.0000   0.0996
  -4.750  -0.2427   0.07510   0.06923  -0.0333   1.0000   0.1035
  -4.250  -0.2030   0.06897   0.06304  -0.0402   0.9967   0.1164
  -3.750  -0.1120   0.06051   0.05419  -0.0568   0.9798   0.1325
  -3.500  -0.0664   0.05681   0.05030  -0.0643   0.9708   0.1482
  -3.250  -0.0182   0.05307   0.04634  -0.0720   0.9621   0.1593
  -2.750   0.0984   0.04448   0.03679  -0.0892   0.9436   0.1036
  -2.500   0.1507   0.04146   0.03340  -0.0957   0.9354   0.1044
  -2.250   0.2067   0.03819   0.02943  -0.1022   0.9251   0.0952
  -2.000   0.2493   0.03576   0.02672  -0.1060   0.9137   0.0938
  -1.750   0.2927   0.03359   0.02419  -0.1095   0.9020   0.0931
  -1.500   0.3355   0.03162   0.02183  -0.1125   0.8900   0.0932
  -1.250   0.3747   0.03012   0.02003  -0.1148   0.8767   0.0983
  -1.000   0.4105   0.02896   0.01867  -0.1163   0.8619   0.1032
  -0.750   0.4465   0.02763   0.01701  -0.1174   0.8467   0.1044
  -0.500   0.4810   0.02648   0.01552  -0.1181   0.8309   0.1062
  -0.250   0.5139   0.02549   0.01419  -0.1184   0.8144   0.1087
   0.000   0.5449   0.02470   0.01314  -0.1182   0.7975   0.1125
   0.250   0.5746   0.02421   0.01247  -0.1179   0.7800   0.1222
   0.500   0.6035   0.02366   0.01177  -0.1173   0.7627   0.1304
   0.750   0.6305   0.02320   0.01112  -0.1165   0.7436   0.1378
   1.000   0.6575   0.02278   0.01061  -0.1157   0.7254   0.1474
   1.250   0.6846   0.02247   0.01020  -0.1150   0.7078   0.1673
   1.500   0.7120   0.02215   0.00988  -0.1145   0.6910   0.1963
   1.750   0.7398   0.02183   0.00961  -0.1141   0.6748   0.2402
   2.000   0.7600   0.02018   0.00940  -0.1124   0.6594   1.0000
   2.250   0.7872   0.02050   0.00931  -0.1117   0.6434   1.0000
   2.500   0.8142   0.02084   0.00939  -0.1112   0.6280   1.0000
   2.750   0.8411   0.02122   0.00959  -0.1108   0.6134   1.0000
   3.000   0.8680   0.02163   0.00983  -0.1104   0.5994   1.0000
   3.250   0.8946   0.02205   0.01015  -0.1100   0.5858   1.0000
   3.500   0.9208   0.02253   0.01059  -0.1097   0.5723   1.0000
   3.750   0.9469   0.02303   0.01107  -0.1094   0.5595   1.0000
   4.000   0.9729   0.02354   0.01157  -0.1091   0.5475   1.0000
   4.250   0.9990   0.02405   0.01212  -0.1088   0.5365   1.0000
   4.500   1.0254   0.02455   0.01262  -0.1085   0.5266   1.0000
   4.750   1.0506   0.02516   0.01333  -0.1082   0.5158   1.0000
   5.000   1.0763   0.02576   0.01401  -0.1079   0.5064   1.0000
   5.250   1.1023   0.02634   0.01469  -0.1076   0.4980   1.0000
   5.500   1.1270   0.02706   0.01559  -0.1073   0.4891   1.0000
   5.750   1.1534   0.02765   0.01626  -0.1070   0.4822   1.0000
   6.000   1.1771   0.02849   0.01739  -0.1066   0.4735   1.0000
   6.250   1.2034   0.02912   0.01815  -0.1063   0.4674   1.0000
   6.500   1.2262   0.03013   0.01947  -0.1059   0.4599   1.0000
   6.750   1.2517   0.03090   0.02045  -0.1056   0.4541   1.0000
   7.000   1.2742   0.03196   0.02184  -0.1051   0.4474   1.0000
   7.250   1.2980   0.03287   0.02311  -0.1046   0.4411   1.0000
   7.500   1.3193   0.03360   0.02417  -0.1035   0.4303   1.0000
   7.750   1.3356   0.03266   0.02321  -0.1004   0.3979   1.0000
   8.000   1.3431   0.03223   0.02276  -0.0965   0.3558   1.0000
   8.250   1.3498   0.03262   0.02325  -0.0932   0.3136   1.0000
   8.500   1.3505   0.03376   0.02430  -0.0896   0.2365   1.0000
   8.750   1.3312   0.03742   0.02668  -0.0850   0.1126   1.0000
   9.000   1.3197   0.04091   0.02998  -0.0814   0.0798   1.0000
   9.250   1.3095   0.04419   0.03323  -0.0784   0.0684   1.0000
   9.500   1.2995   0.04771   0.03682  -0.0762   0.0629   1.0000
   9.750   1.2884   0.05162   0.04089  -0.0748   0.0594   1.0000
  10.000   1.2797   0.05559   0.04507  -0.0741   0.0561   1.0000
  10.250   1.2704   0.05992   0.04958  -0.0739   0.0532   1.0000
  10.500   1.2607   0.06450   0.05430  -0.0741   0.0509   1.0000
  10.750   1.2502   0.06929   0.05920  -0.0745   0.0488   1.0000
  11.000   1.2426   0.07367   0.06366  -0.0746   0.0470   1.0000
  11.250   1.2406   0.07726   0.06745  -0.0742   0.0451   1.0000
  11.500   1.2405   0.08044   0.07079  -0.0734   0.0434   1.0000
  11.750   1.2426   0.08327   0.07375  -0.0723   0.0414   1.0000
  12.000   1.2459   0.08587   0.07641  -0.0710   0.0393   1.0000
  12.250   1.2546   0.08752   0.07802  -0.0685   0.0368   1.0000
  12.500   1.2655   0.08956   0.08038  -0.0667   0.0350   1.0000
  12.750   1.2818   0.09113   0.08225  -0.0641   0.0336   1.0000
  13.000   1.2928   0.09375   0.08516  -0.0624   0.0327   1.0000
  13.250   1.2961   0.09746   0.08914  -0.0621   0.0319   1.0000
  13.500   1.2945   0.10178   0.09371  -0.0626   0.0313   1.0000
  13.750   1.2904   0.10648   0.09872  -0.0636   0.0306   1.0000
  14.000   1.2834   0.11168   0.10414  -0.0653   0.0302   1.0000
  14.250   1.2745   0.11733   0.11001  -0.0676   0.0299   1.0000
  14.500   1.2640   0.12349   0.11639  -0.0706   0.0297   1.0000
  14.750   1.2509   0.13054   0.12368  -0.0746   0.0297   1.0000
  15.000   1.2345   0.13890   0.13227  -0.0799   0.0301   1.0000
  15.250   1.2112   0.15013   0.14370  -0.0878   0.0312   1.0000
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