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GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 417 AIRFOIL (goe417-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.87 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe417-il-1000000-n5.txt
Download as CSV file: xf-goe417-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1757   0.10960   0.10805  -0.0418   0.9897   0.0058
 -10.750  -0.1674   0.10589   0.10433  -0.0437   0.9880   0.0059
 -10.500  -0.2924   0.12023   0.11859  -0.0271   0.9997   0.0038
 -10.250  -0.2777   0.11723   0.11560  -0.0299   0.9988   0.0058
  -9.750  -0.2563   0.10917   0.10754  -0.0353   0.9943   0.0039
  -9.500  -0.2451   0.10519   0.10356  -0.0381   0.9914   0.0040
  -9.250  -0.2297   0.10304   0.10142  -0.0406   0.9888   0.0046
  -9.000  -0.2181   0.09860   0.09698  -0.0440   0.9861   0.0043
  -8.750  -0.2027   0.09679   0.09516  -0.0460   0.9821   0.0053
  -8.500  -0.1884   0.09319   0.09157  -0.0494   0.9787   0.0049
  -8.250  -0.1717   0.08966   0.08803  -0.0532   0.9758   0.0050
  -8.000  -0.1548   0.08578   0.08415  -0.0575   0.9708   0.0047
  -7.750  -0.1314   0.08104   0.07940  -0.0642   0.9663   0.0045
  -7.500  -0.1091   0.07747   0.07581  -0.0695   0.9587   0.0048
  -7.250  -0.0879   0.07325   0.07155  -0.0757   0.9490   0.0046
  -7.000  -0.0679   0.06987   0.06813  -0.0804   0.9364   0.0048
  -6.750  -0.0525   0.06671   0.06493  -0.0839   0.9229   0.0051
  -6.500  -0.0385   0.06345   0.06161  -0.0870   0.9079   0.0053
  -6.250  -0.0237   0.05985   0.05796  -0.0904   0.8938   0.0055
  -6.000  -0.0073   0.05545   0.05348  -0.0947   0.8798   0.0060
  -5.750   0.0122   0.05274   0.05070  -0.0976   0.8667   0.0062
  -5.500   0.0332   0.05017   0.04806  -0.1004   0.8534   0.0064
  -5.250   0.0558   0.04742   0.04521  -0.1033   0.8403   0.0068
  -5.000   0.0804   0.04403   0.04171  -0.1068   0.8250   0.0074
  -4.750   0.1116   0.03755   0.03503  -0.1134   0.8122   0.0084
  -4.500   0.1377   0.03569   0.03307  -0.1151   0.7995   0.0088
  -4.250   0.1642   0.03399   0.03127  -0.1166   0.7884   0.0093
  -4.000   0.2001   0.02701   0.02396  -0.1218   0.7777   0.0114
  -3.750   0.2266   0.02577   0.02260  -0.1224   0.7644   0.0118
  -3.500   0.2531   0.02460   0.02130  -0.1229   0.7490   0.0123
  -3.250   0.2860   0.01744   0.01356  -0.1251   0.7358   0.0155
  -3.000   0.3115   0.01704   0.01302  -0.1249   0.7152   0.0158
  -2.750   0.3365   0.01672   0.01253  -0.1245   0.6887   0.0163
  -2.250   0.3886   0.01296   0.00794  -0.1236   0.6395   0.0197
  -2.000   0.4144   0.01211   0.00677  -0.1233   0.6198   0.0202
  -1.750   0.4402   0.01129   0.00574  -0.1230   0.6040   0.0206
  -1.500   0.4663   0.01091   0.00521  -0.1227   0.5887   0.0209
  -1.250   0.4926   0.01067   0.00487  -0.1224   0.5735   0.0213
  -1.000   0.5187   0.01051   0.00458  -0.1220   0.5542   0.0218
  -0.750   0.5443   0.01025   0.00414  -0.1215   0.5286   0.0223
  -0.250   0.5953   0.00995   0.00347  -0.1205   0.4721   0.0235
   0.000   0.6210   0.00982   0.00320  -0.1201   0.4499   0.0239
   0.250   0.6468   0.00974   0.00299  -0.1196   0.4278   0.0243
   0.500   0.6724   0.00968   0.00281  -0.1192   0.4067   0.0246
   0.750   0.6978   0.00966   0.00266  -0.1187   0.3839   0.0248
   1.500   0.7748   0.00968   0.00242  -0.1174   0.3348   0.0255
   2.000   0.8264   0.00967   0.00228  -0.1166   0.3091   0.0256
   2.250   0.8525   0.00967   0.00226  -0.1163   0.3018   0.0258
   2.500   0.8789   0.00968   0.00224  -0.1160   0.2961   0.0260
   2.750   0.9049   0.00974   0.00228  -0.1156   0.2899   0.0263
   3.250   0.9574   0.00977   0.00229  -0.1150   0.2787   0.0289
   3.500   0.9834   0.00986   0.00236  -0.1147   0.2729   0.0301
   3.750   1.0095   0.00995   0.00245  -0.1144   0.2668   0.0310
   4.000   1.0352   0.01008   0.00255  -0.1140   0.2597   0.0318
   4.250   1.0612   0.01018   0.00266  -0.1136   0.2531   0.0333
   4.500   1.0863   0.01035   0.00279  -0.1132   0.2413   0.0345
   4.750   1.1110   0.01058   0.00296  -0.1127   0.2247   0.0353
   5.000   1.1357   0.01080   0.00314  -0.1122   0.2116   0.0442
   5.500   1.1842   0.01022   0.00394  -0.1117   0.1704   1.0000
   5.750   1.2059   0.01074   0.00429  -0.1107   0.1441   1.0000
   6.000   1.2291   0.01110   0.00458  -0.1100   0.1305   1.0000
   6.250   1.2527   0.01143   0.00485  -0.1094   0.1207   1.0000
   6.500   1.2764   0.01172   0.00513  -0.1087   0.1123   1.0000
   6.750   1.2994   0.01208   0.00543  -0.1080   0.1027   1.0000
   7.000   1.3167   0.01300   0.00607  -0.1064   0.0566   1.0000
   7.250   1.3360   0.01370   0.00668  -0.1051   0.0344   1.0000
   7.500   1.3551   0.01441   0.00730  -0.1038   0.0147   1.0000
   7.750   1.3773   0.01478   0.00770  -0.1029   0.0114   1.0000
   8.000   1.3986   0.01523   0.00816  -0.1019   0.0093   1.0000
   8.250   1.4195   0.01568   0.00864  -0.1009   0.0079   1.0000
   8.500   1.4406   0.01609   0.00909  -0.0998   0.0071   1.0000
   8.750   1.4607   0.01656   0.00961  -0.0987   0.0064   1.0000
   9.000   1.4793   0.01715   0.01023  -0.0973   0.0055   1.0000
   9.250   1.4988   0.01761   0.01074  -0.0961   0.0052   1.0000
   9.500   1.5174   0.01812   0.01130  -0.0947   0.0048   1.0000
   9.750   1.5352   0.01863   0.01185  -0.0932   0.0043   1.0000
  10.000   1.5504   0.01921   0.01246  -0.0913   0.0040   1.0000
  10.250   1.5626   0.01991   0.01324  -0.0888   0.0037   1.0000
  10.500   1.5742   0.02064   0.01405  -0.0864   0.0035   1.0000
  10.750   1.5867   0.02132   0.01480  -0.0841   0.0034   1.0000
  11.000   1.5983   0.02206   0.01561  -0.0818   0.0032   1.0000
  11.250   1.6081   0.02291   0.01655  -0.0794   0.0031   1.0000
  11.500   1.6180   0.02378   0.01750  -0.0771   0.0029   1.0000
  11.750   1.6270   0.02474   0.01853  -0.0748   0.0028   1.0000
  12.000   1.6347   0.02581   0.01969  -0.0725   0.0027   1.0000
  12.250   1.6422   0.02692   0.02088  -0.0703   0.0026   1.0000
  12.500   1.6488   0.02815   0.02219  -0.0682   0.0025   1.0000
  12.750   1.6529   0.02962   0.02374  -0.0660   0.0023   1.0000
  13.000   1.6517   0.03160   0.02583  -0.0636   0.0022   1.0000
  13.250   1.6508   0.03367   0.02802  -0.0615   0.0022   1.0000
  13.500   1.6517   0.03570   0.03016  -0.0598   0.0021   1.0000
  13.750   1.6533   0.03778   0.03234  -0.0584   0.0021   1.0000
  14.000   1.6499   0.04049   0.03518  -0.0571   0.0020   1.0000
  14.250   1.6493   0.04307   0.03787  -0.0563   0.0020   1.0000
  14.500   1.6422   0.04658   0.04152  -0.0557   0.0020   1.0000
  14.750   1.6386   0.04990   0.04496  -0.0555   0.0019   1.0000
  15.000   1.6299   0.05415   0.04935  -0.0558   0.0019   1.0000
  15.250   1.6195   0.05890   0.05424  -0.0567   0.0018   1.0000
  15.500   1.6091   0.06393   0.05941  -0.0579   0.0018   1.0000
  15.750   1.6007   0.06889   0.06449  -0.0593   0.0018   1.0000
  16.000   1.5863   0.07502   0.07076  -0.0614   0.0018   1.0000
  16.250   1.5713   0.08153   0.07742  -0.0638   0.0018   1.0000
  16.500   1.5570   0.08812   0.08414  -0.0664   0.0018   1.0000
  16.750   1.5425   0.09487   0.09103  -0.0693   0.0017   1.0000
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