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GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 528 AIRFOIL (goe528-il)
Reynolds number: 100,000
Max Cl/Cd: 46.58 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe528-il-100000.txt
Download as CSV file: xf-goe528-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 528 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2618   0.11825   0.11382  -0.0307   1.0000   0.0806
  -9.250  -0.2761   0.11784   0.11351  -0.0282   1.0000   0.0817
  -9.000  -0.2925   0.11766   0.11342  -0.0262   1.0000   0.0829
  -8.750  -0.2997   0.11721   0.11302  -0.0362   0.9923   0.0847
  -8.500  -0.2769   0.11083   0.10664  -0.0394   0.9874   0.0860
  -8.250  -0.2402   0.10542   0.10117  -0.0401   0.9845   0.0893
  -8.000  -0.2205   0.10187   0.09761  -0.0446   0.9770   0.0941
  -7.750  -0.2209   0.10026   0.09603  -0.0540   0.9644   0.0982
  -7.500  -0.2133   0.09590   0.09168  -0.0629   0.9526   0.0998
  -7.250  -0.1761   0.09085   0.08660  -0.0597   0.9512   0.1031
  -7.000  -0.1506   0.08706   0.08278  -0.0646   0.9448   0.1079
  -6.750  -0.1492   0.08478   0.08033  -0.0853   0.9235   0.1143
  -6.500  -0.1249   0.07929   0.07498  -0.0794   0.9205   0.1164
  -6.250  -0.0922   0.07581   0.07148  -0.0801   0.9161   0.1232
  -6.000  -0.0769   0.07160   0.06713  -0.0929   0.9024   0.1317
  -5.750  -0.0426   0.06791   0.06347  -0.0921   0.8994   0.1364
  -5.500  -0.0224   0.06425   0.05960  -0.1022   0.8867   0.1483
  -5.250   0.0095   0.06083   0.05624  -0.1016   0.8825   0.1531
  -5.000   0.0288   0.05777   0.05301  -0.1068   0.8706   0.1662
  -4.750   0.0623   0.05465   0.04974  -0.1113   0.8643   0.1827
  -4.500   0.0777   0.05268   0.04785  -0.1084   0.8538   0.1888
  -4.250   0.1094   0.04970   0.04476  -0.1116   0.8472   0.2056
  -4.000   0.1250   0.04780   0.04278  -0.1115   0.8351   0.2210
  -3.750   0.1588   0.04557   0.04032  -0.1150   0.8290   0.2518
  -3.500   0.1709   0.04389   0.03873  -0.1119   0.8168   0.2605
  -3.250   0.2339   0.03369   0.02667  -0.1237   0.8118   0.1274
  -3.000   0.2541   0.03126   0.02363  -0.1221   0.7997   0.1119
  -2.750   0.2908   0.02882   0.02080  -0.1231   0.7948   0.1076
  -2.500   0.3103   0.02775   0.01943  -0.1214   0.7827   0.1059
  -2.250   0.3425   0.02653   0.01790  -0.1215   0.7759   0.1081
  -2.000   0.3670   0.02571   0.01684  -0.1205   0.7658   0.1093
  -1.750   0.3980   0.02473   0.01562  -0.1203   0.7586   0.1106
  -1.500   0.4234   0.02413   0.01484  -0.1194   0.7491   0.1129
  -1.250   0.4532   0.02323   0.01392  -0.1192   0.7420   0.1185
  -1.000   0.4771   0.02285   0.01354  -0.1182   0.7326   0.1264
  -0.750   0.5070   0.02209   0.01280  -0.1179   0.7262   0.1370
  -0.500   0.5282   0.02178   0.01258  -0.1165   0.7165   0.1559
  -0.250   0.5939   0.01848   0.01158  -0.1226   0.7118   1.0000
   0.000   0.6118   0.01893   0.01183  -0.1208   0.7013   1.0000
   0.250   0.6441   0.01887   0.01145  -0.1210   0.6955   1.0000
   0.500   0.6619   0.01936   0.01183  -0.1192   0.6855   1.0000
   0.750   0.6934   0.01933   0.01155  -0.1194   0.6795   1.0000
   1.000   0.7119   0.01982   0.01197  -0.1178   0.6701   1.0000
   1.250   0.7421   0.01985   0.01180  -0.1177   0.6639   1.0000
   1.500   0.7620   0.02032   0.01219  -0.1164   0.6552   1.0000
   1.750   0.7905   0.02042   0.01214  -0.1162   0.6484   1.0000
   2.000   0.8129   0.02081   0.01247  -0.1151   0.6406   1.0000
   2.250   0.8388   0.02102   0.01257  -0.1146   0.6331   1.0000
   2.500   0.8649   0.02127   0.01272  -0.1141   0.6263   1.0000
   2.750   0.8868   0.02166   0.01307  -0.1130   0.6181   1.0000
   3.000   0.9189   0.02168   0.01294  -0.1133   0.6124   1.0000
   3.250   0.9351   0.02231   0.01362  -0.1115   0.6031   1.0000
   3.500   0.9683   0.02228   0.01342  -0.1120   0.5973   1.0000
   3.750   0.9835   0.02297   0.01419  -0.1100   0.5880   1.0000
   4.000   1.0155   0.02298   0.01407  -0.1104   0.5818   1.0000
   4.250   1.0320   0.02364   0.01479  -0.1086   0.5729   1.0000
   4.500   1.0624   0.02371   0.01477  -0.1087   0.5662   1.0000
   4.750   1.0804   0.02433   0.01544  -0.1072   0.5576   1.0000
   5.000   1.1090   0.02448   0.01552  -0.1070   0.5505   1.0000
   5.250   1.1284   0.02506   0.01614  -0.1057   0.5422   1.0000
   5.500   1.1549   0.02530   0.01634  -0.1053   0.5346   1.0000
   5.750   1.1760   0.02583   0.01690  -0.1042   0.5268   1.0000
   6.000   1.2001   0.02616   0.01724  -0.1035   0.5187   1.0000
   6.250   1.2229   0.02663   0.01773  -0.1027   0.5112   1.0000
   6.500   1.2438   0.02711   0.01824  -0.1016   0.5029   1.0000
   6.750   1.2696   0.02749   0.01861  -0.1012   0.4958   1.0000
   7.000   1.2860   0.02815   0.01938  -0.0995   0.4872   1.0000
   7.250   1.3161   0.02836   0.01954  -0.0997   0.4806   1.0000
   7.500   1.3271   0.02920   0.02053  -0.0973   0.4714   1.0000
   7.750   1.3621   0.02924   0.02048  -0.0982   0.4652   1.0000
   8.000   1.3664   0.03036   0.02183  -0.0949   0.4561   1.0000
   8.250   1.4023   0.03037   0.02175  -0.0959   0.4500   1.0000
   8.500   1.4038   0.03167   0.02328  -0.0923   0.4413   1.0000
   8.750   1.4383   0.03159   0.02315  -0.0931   0.4346   1.0000
   9.000   1.4412   0.03274   0.02450  -0.0897   0.4259   1.0000
   9.250   1.4779   0.03240   0.02406  -0.0906   0.4185   1.0000
   9.500   1.4775   0.03362   0.02550  -0.0868   0.4099   1.0000
   9.750   1.5143   0.03330   0.02511  -0.0878   0.4026   1.0000
  10.000   1.5113   0.03464   0.02668  -0.0837   0.3947   1.0000
  10.250   1.5456   0.03437   0.02636  -0.0843   0.3873   1.0000
  10.500   1.5429   0.03573   0.02794  -0.0804   0.3801   1.0000
  10.750   1.5679   0.03585   0.02808  -0.0799   0.3729   1.0000
  11.000   1.5736   0.03682   0.02919  -0.0770   0.3660   1.0000
  11.250   1.5835   0.03745   0.02991  -0.0746   0.3590   1.0000
  11.500   1.6031   0.03783   0.03035  -0.0734   0.3521   1.0000
  11.750   1.5938   0.03915   0.03183  -0.0688   0.3456   1.0000
  12.000   1.6267   0.03884   0.03149  -0.0692   0.3377   1.0000
  12.250   1.6056   0.04080   0.03368  -0.0636   0.3318   1.0000
  12.500   1.6417   0.04007   0.03287  -0.0642   0.3229   1.0000
  12.750   1.6146   0.04256   0.03562  -0.0587   0.3173   1.0000
  13.000   1.6495   0.04174   0.03473  -0.0589   0.3079   1.0000
  13.250   1.6187   0.04478   0.03805  -0.0541   0.3027   1.0000
  13.500   1.6439   0.04419   0.03740  -0.0533   0.2925   1.0000
  13.750   1.6134   0.04767   0.04114  -0.0495   0.2868   1.0000
  14.000   1.6236   0.04795   0.04141  -0.0479   0.2762   1.0000
  14.250   1.6036   0.05100   0.04463  -0.0455   0.2683   1.0000
  14.500   1.5945   0.05324   0.04695  -0.0438   0.2587   1.0000
  14.750   1.5919   0.05486   0.04856  -0.0424   0.2472   1.0000
  15.000   1.5669   0.05926   0.05315  -0.0413   0.2383   1.0000
  15.250   1.5494   0.06315   0.05712  -0.0407   0.2277   1.0000
  15.500   1.5350   0.06692   0.06092  -0.0404   0.2155   1.0000
  15.750   1.5190   0.07120   0.06520  -0.0405   0.2026   1.0000
  16.000   1.5015   0.07601   0.07001  -0.0410   0.1893   1.0000
  16.250   1.4842   0.08110   0.07506  -0.0418   0.1758   1.0000
  16.500   1.4689   0.08611   0.08002  -0.0427   0.1631   1.0000
  16.750   1.4502   0.09204   0.08602  -0.0442   0.1521   1.0000
  17.000   1.4358   0.09744   0.09144  -0.0456   0.1418   1.0000
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