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GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 373 AIRFOIL (goe373-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.98 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe373-il-1000000.txt
Download as CSV file: xf-goe373-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 373 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3025   0.09276   0.09122  -0.0217   1.0000   0.0128
  -7.750  -0.3048   0.09067   0.08917  -0.0210   1.0000   0.0128
  -7.500  -0.3133   0.08913   0.08766  -0.0191   1.0000   0.0128
  -7.250  -0.2902   0.08448   0.08301  -0.0272   0.9973   0.0128
  -4.500   0.0256   0.04203   0.03961  -0.0886   0.8158   0.0168
  -4.250   0.0495   0.03970   0.03715  -0.0902   0.7991   0.0172
  -4.000   0.0749   0.03729   0.03460  -0.0918   0.7843   0.0180
  -3.750   0.1112   0.03457   0.03163  -0.0940   0.7716   0.0193
  -3.500   0.1405   0.03190   0.02875  -0.0951   0.7593   0.0194
  -3.250   0.1675   0.02957   0.02623  -0.0957   0.7474   0.0194
  -3.000   0.1942   0.02739   0.02386  -0.0961   0.7360   0.0195
  -2.750   0.2186   0.02389   0.02015  -0.0967   0.7251   0.0197
  -2.500   0.2423   0.02230   0.01845  -0.0970   0.7126   0.0199
  -2.250   0.2672   0.02098   0.01700  -0.0971   0.6991   0.0201
  -2.000   0.2928   0.01974   0.01562  -0.0971   0.6843   0.0205
  -1.750   0.3190   0.01855   0.01426  -0.0970   0.6684   0.0211
  -1.500   0.3459   0.01738   0.01290  -0.0967   0.6512   0.0223
  -1.250   0.3756   0.01696   0.01214  -0.0957   0.6318   0.0236
  -1.000   0.4020   0.01618   0.01111  -0.0953   0.6107   0.0236
  -0.750   0.4283   0.01545   0.01014  -0.0949   0.5886   0.0237
  -0.500  -0.1596   0.09651   0.09287  -0.0608   0.7056   0.0194
   0.000   0.5059   0.01208   0.00622  -0.0940   0.5380   0.0245
   0.250   0.5322   0.01154   0.00559  -0.0937   0.5247   0.0250
   0.500   0.5589   0.01110   0.00505  -0.0934   0.5128   0.0257
   0.750   0.5857   0.01076   0.00461  -0.0931   0.5023   0.0270
   1.000   0.6133   0.01120   0.00487  -0.0926   0.4922   0.0288
   1.250   0.6397   0.01003   0.00365  -0.0924   0.4827   0.0302
   1.500   0.6662   0.00971   0.00332  -0.0921   0.4718   0.0316
   1.750   0.6928   0.00959   0.00314  -0.0918   0.4597   0.0336
   2.500   0.7716   0.00894   0.00240  -0.0908   0.4181   0.0470
   2.750   0.7977   0.00888   0.00231  -0.0904   0.4023   0.0504
   3.000   0.8238   0.00885   0.00223  -0.0900   0.3872   0.0516
   3.500   0.8761   0.00900   0.00219  -0.0891   0.3560   0.0377
   3.750   0.9019   0.00915   0.00225  -0.0886   0.3360   0.0337
   4.000   0.9277   0.00924   0.00227  -0.0882   0.3210   0.0333
   4.250   0.9537   0.00934   0.00233  -0.0878   0.3094   0.0340
   4.500   0.9796   0.00948   0.00242  -0.0875   0.2963   0.0345
   4.750   1.0054   0.00963   0.00253  -0.0871   0.2813   0.0358
   5.000   1.0309   0.00982   0.00264  -0.0867   0.2627   0.0357
   5.250   1.0548   0.01020   0.00284  -0.0861   0.2252   0.0360
   5.500   1.0747   0.01104   0.00329  -0.0850   0.1604   0.0370
   5.750   1.0973   0.01156   0.00365  -0.0842   0.1292   0.0435
   6.000   1.1165   0.01142   0.00465  -0.0837   0.0502   1.0000
   6.250   1.1369   0.01223   0.00525  -0.0825   0.0165   1.0000
   6.500   1.1614   0.01253   0.00559  -0.0819   0.0151   1.0000
   6.750   1.1854   0.01288   0.00599  -0.0812   0.0140   1.0000
   7.000   1.2086   0.01331   0.00646  -0.0805   0.0129   1.0000
   7.250   1.2305   0.01388   0.00710  -0.0795   0.0117   1.0000
   7.500   1.2527   0.01439   0.00769  -0.0786   0.0113   1.0000
   7.750   1.2751   0.01485   0.00818  -0.0777   0.0109   1.0000
   8.000   1.2968   0.01538   0.00876  -0.0768   0.0105   1.0000
   8.250   1.3176   0.01596   0.00939  -0.0757   0.0101   1.0000
   8.500   1.3376   0.01660   0.01010  -0.0745   0.0096   1.0000
   8.750   1.3567   0.01729   0.01084  -0.0732   0.0092   1.0000
   9.000   1.3728   0.01821   0.01182  -0.0715   0.0087   1.0000
   9.250   1.3774   0.02000   0.01373  -0.0681   0.0082   1.0000
   9.500   1.3940   0.02070   0.01448  -0.0665   0.0080   1.0000
   9.750   1.4092   0.02145   0.01529  -0.0647   0.0079   1.0000
  10.000   1.4208   0.02234   0.01626  -0.0624   0.0078   1.0000
  10.250   1.4291   0.02320   0.01719  -0.0595   0.0076   1.0000
  10.500   1.4348   0.02421   0.01826  -0.0563   0.0074   1.0000
  10.750   1.4410   0.02523   0.01935  -0.0535   0.0073   1.0000
  11.000   1.4450   0.02649   0.02068  -0.0507   0.0071   1.0000
  11.250   1.4480   0.02791   0.02218  -0.0480   0.0069   1.0000
  11.500   1.4507   0.02949   0.02385  -0.0457   0.0069   1.0000
  11.750   1.4538   0.03115   0.02558  -0.0438   0.0067   1.0000
  12.000   1.4560   0.03304   0.02754  -0.0421   0.0066   1.0000
  12.250   1.4591   0.03495   0.02952  -0.0408   0.0064   1.0000
  12.500   1.4614   0.03705   0.03170  -0.0396   0.0063   1.0000
  12.750   1.4628   0.03938   0.03411  -0.0386   0.0062   1.0000
  13.000   1.4636   0.04185   0.03664  -0.0379   0.0060   1.0000
  13.250   1.4639   0.04453   0.03938  -0.0372   0.0059   1.0000
  13.500   1.4690   0.04800   0.04288  -0.0350   0.0056   1.0000
  13.750   1.4682   0.05071   0.04572  -0.0347   0.0056   1.0000
  14.000   1.4638   0.05372   0.04888  -0.0350   0.0055   1.0000
  14.250   1.4635   0.05676   0.05203  -0.0351   0.0055   1.0000
  14.500   1.4593   0.06024   0.05565  -0.0358   0.0054   1.0000
  14.750   1.4576   0.06377   0.05930  -0.0361   0.0054   1.0000
  15.000   1.4540   0.06763   0.06329  -0.0367   0.0054   1.0000
  15.250   1.4479   0.07192   0.06772  -0.0379   0.0053   1.0000
  15.500   1.4420   0.07640   0.07234  -0.0392   0.0053   1.0000
  15.750   1.4341   0.08132   0.07740  -0.0409   0.0053   1.0000
  16.000   1.4254   0.08650   0.08273  -0.0431   0.0053   1.0000
  16.250   1.4159   0.09203   0.08840  -0.0454   0.0053   1.0000
  16.500   1.4053   0.09793   0.09445  -0.0481   0.0053   1.0000
  16.750   1.3935   0.10425   0.10092  -0.0514   0.0053   1.0000
  17.000   1.3827   0.11055   0.10736  -0.0548   0.0053   1.0000
  17.250   1.3692   0.11758   0.11453  -0.0584   0.0054   1.0000
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