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GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 375 AIRFOIL (goe375-il)
Reynolds number: 50,000
Max Cl/Cd: 32.61 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe375-il-50000.txt
Download as CSV file: xf-goe375-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 375 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3980   0.11811   0.11121  -0.0071   1.0000   0.0805
  -9.000  -0.4008   0.11723   0.11043  -0.0097   1.0000   0.0814
  -8.750  -0.4044   0.11627   0.10959  -0.0123   1.0000   0.0818
  -8.500  -0.3794   0.10757   0.10083  -0.0088   1.0000   0.0878
  -8.250  -0.3750   0.10492   0.09824  -0.0097   1.0000   0.0909
  -8.000  -0.3760   0.10307   0.09650  -0.0113   1.0000   0.0941
  -7.750  -0.3811   0.10218   0.09573  -0.0149   1.0000   0.0957
  -7.500  -0.3737   0.09792   0.09155  -0.0150   1.0000   0.0979
  -7.250  -0.3630   0.09379   0.08745  -0.0132   1.0000   0.1038
  -7.000  -0.3611   0.09195   0.08569  -0.0172   1.0000   0.1091
  -6.750  -0.3561   0.08939   0.08321  -0.0210   1.0000   0.1114
  -6.500  -0.3461   0.08496   0.07884  -0.0174   1.0000   0.1191
  -6.250  -0.3394   0.08438   0.07822  -0.0256   1.0000   0.1248
  -6.000  -0.3321   0.07904   0.07305  -0.0198   1.0000   0.1347
  -5.750  -0.3249   0.07599   0.07006  -0.0210   1.0000   0.1439
  -5.500  -0.3167   0.07332   0.06742  -0.0228   1.0000   0.1565
  -5.250  -0.3096   0.07021   0.06437  -0.0219   1.0000   0.1727
  -5.000  -0.3023   0.06732   0.06155  -0.0208   1.0000   0.1908
  -4.750   0.0127   0.04126   0.03488  -0.0156   1.0000   1.0000
  -4.500   0.0240   0.03936   0.03303  -0.0164   1.0000   1.0000
  -4.250   0.0352   0.03751   0.03126  -0.0172   1.0000   1.0000
  -4.000   0.0464   0.03576   0.02958  -0.0179   1.0000   1.0000
  -3.750   0.0573   0.03407   0.02798  -0.0186   1.0000   1.0000
  -3.500   0.0679   0.03246   0.02645  -0.0192   1.0000   1.0000
  -3.250   0.0580   0.03202   0.02617  -0.0149   1.0000   0.9910
  -3.000   0.0132   0.03323   0.02764  -0.0029   1.0000   0.9622
  -2.750  -0.0297   0.03387   0.02854   0.0076   1.0000   0.9338
  -2.500  -0.0717   0.03424   0.02918   0.0174   1.0000   0.9136
  -2.250  -0.1117   0.03421   0.02942   0.0263   1.0000   0.8962
  -2.000  -0.1524   0.03400   0.02945   0.0352   1.0000   0.8852
  -1.750  -0.2035   0.03387   0.02954   0.0456   1.0000   0.8731
  -1.500  -0.2705   0.03390   0.02983   0.0581   1.0000   0.8568
  -1.250  -0.1008   0.03103   0.02529  -0.0125   1.0000   0.5103
  -1.000  -0.0236   0.03019   0.02315  -0.0262   1.0000   0.3549
  -0.750   0.0157   0.02998   0.02210  -0.0288   1.0000   0.2865
  -0.500   0.0422   0.02936   0.02112  -0.0291   1.0000   0.2485
  -0.250   0.0724   0.02917   0.02049  -0.0302   0.9974   0.2176
   0.000   0.1556   0.02856   0.01913  -0.0392   0.9715   0.1851
   0.250   0.2322   0.02761   0.01771  -0.0469   0.9433   0.1695
   0.500   0.3114   0.02627   0.01610  -0.0545   0.9151   0.1597
   0.750   0.3850   0.02500   0.01474  -0.0610   0.8870   0.1630
   1.000   0.4456   0.02394   0.01358  -0.0649   0.8579   0.1649
   1.250   0.4957   0.02311   0.01269  -0.0667   0.8271   0.1716
   1.500   0.5359   0.02245   0.01209  -0.0667   0.7952   0.1932
   1.750   0.5803   0.02048   0.01172  -0.0677   0.7579   1.0000
   2.000   0.6069   0.02057   0.01146  -0.0653   0.7234   1.0000
   2.250   0.6323   0.02068   0.01122  -0.0630   0.6902   1.0000
   2.500   0.6557   0.02094   0.01118  -0.0607   0.6559   1.0000
   2.750   0.6798   0.02126   0.01118  -0.0587   0.6240   1.0000
   3.000   0.7038   0.02173   0.01135  -0.0569   0.5940   1.0000
   3.250   0.7276   0.02234   0.01166  -0.0553   0.5658   1.0000
   3.500   0.7517   0.02305   0.01210  -0.0540   0.5407   1.0000
   3.750   0.7754   0.02382   0.01265  -0.0527   0.5170   1.0000
   4.000   0.7987   0.02472   0.01345  -0.0516   0.4955   1.0000
   4.250   0.8219   0.02563   0.01423  -0.0506   0.4753   1.0000
   4.500   0.8456   0.02654   0.01501  -0.0496   0.4575   1.0000
   4.750   0.8693   0.02751   0.01587  -0.0487   0.4412   1.0000
   5.000   0.8926   0.02855   0.01686  -0.0478   0.4258   1.0000
   5.250   0.9152   0.02970   0.01808  -0.0470   0.4114   1.0000
   5.500   0.9371   0.03090   0.01934  -0.0461   0.3974   1.0000
   5.750   0.9580   0.03227   0.02083  -0.0453   0.3846   1.0000
   6.000   0.9779   0.03396   0.02270  -0.0446   0.3739   1.0000
   6.250   1.0002   0.03543   0.02427  -0.0438   0.3646   1.0000
   6.500   1.0196   0.03712   0.02614  -0.0430   0.3547   1.0000
   6.750   1.0356   0.03929   0.02857  -0.0422   0.3455   1.0000
   7.000   1.0597   0.04059   0.02986  -0.0415   0.3379   1.0000
   7.250   1.0667   0.04410   0.03386  -0.0408   0.3318   1.0000
   7.500   1.0797   0.04694   0.03695  -0.0402   0.3266   1.0000
   7.750   1.0962   0.04941   0.03962  -0.0396   0.3217   1.0000
   8.000   1.0851   0.05502   0.04568  -0.0394   0.3178   1.0000
   8.250   1.0738   0.06055   0.05147  -0.0395   0.3143   1.0000
   8.500   1.0295   0.07013   0.06116  -0.0417   0.3155   1.0000
   8.750   0.9830   0.08033   0.07131  -0.0454   0.3205   1.0000
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