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GOE 409 AIRFOIL (goe409-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 409 AIRFOIL (goe409-il)
Reynolds number: 50,000
Max Cl/Cd: 28.72 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe409-il-50000.txt
Download as CSV file: xf-goe409-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 409 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6213   0.09370   0.08586  -0.0256   1.0000   0.2044
 -10.250  -0.6221   0.08816   0.08033  -0.0271   1.0000   0.2000
 -10.000  -0.8112   0.07067   0.06285  -0.0325   1.0000   0.1744
  -9.750  -0.8189   0.06646   0.05854  -0.0307   1.0000   0.1734
  -9.500  -0.8292   0.06249   0.05443  -0.0282   1.0000   0.1722
  -9.250  -0.8406   0.05874   0.05048  -0.0252   1.0000   0.1710
  -9.000  -0.8509   0.05530   0.04677  -0.0217   1.0000   0.1703
  -8.750  -0.8586   0.05220   0.04334  -0.0180   1.0000   0.1708
  -8.500  -0.8625   0.04936   0.04014  -0.0144   1.0000   0.1718
  -8.250  -0.8622   0.04668   0.03707  -0.0110   1.0000   0.1729
  -8.000  -0.8577   0.04413   0.03413  -0.0079   1.0000   0.1737
  -7.750  -0.8497   0.04177   0.03135  -0.0050   1.0000   0.1745
  -7.500  -0.8322   0.03932   0.02881  -0.0036   1.0000   0.1768
  -7.250  -0.8140   0.03748   0.02690  -0.0021   1.0000   0.1809
  -7.000  -0.7982   0.03577   0.02493  -0.0001   1.0000   0.1859
  -6.750  -0.7822   0.03414   0.02289   0.0020   1.0000   0.1899
  -6.500  -0.7570   0.03233   0.02117   0.0025   1.0000   0.1953
  -6.250  -0.7336   0.03087   0.01958   0.0035   1.0000   0.2022
  -6.000  -0.7081   0.02942   0.01816   0.0042   1.0000   0.2118
  -5.750  -0.6842   0.02812   0.01693   0.0051   1.0000   0.2265
  -5.500  -0.6608   0.02676   0.01574   0.0061   1.0000   0.2487
  -5.250  -0.6417   0.02501   0.01448   0.0079   1.0000   0.2926
  -5.000  -0.6410   0.02308   0.01370   0.0129   1.0000   0.3986
  -4.750  -0.6420   0.02235   0.01364   0.0193   1.0000   0.5201
  -4.500  -0.6323   0.02233   0.01395   0.0245   1.0000   0.5994
  -4.250  -0.6175   0.02275   0.01453   0.0292   1.0000   0.6596
  -4.000  -0.5968   0.02354   0.01535   0.0333   1.0000   0.7087
  -3.750  -0.5700   0.02443   0.01617   0.0361   1.0000   0.7472
  -3.500  -0.5367   0.02553   0.01713   0.0379   1.0000   0.7816
  -3.250  -0.4853   0.02726   0.01864   0.0374   1.0000   0.8166
  -3.000  -0.3495   0.03056   0.02145   0.0244   1.0000   0.8611
  -2.750  -0.2662   0.03104   0.02163   0.0158   1.0000   0.8904
  -2.500  -0.1891   0.03091   0.02128   0.0072   1.0000   0.9211
  -2.250  -0.1198   0.03021   0.02041  -0.0012   1.0000   0.9483
  -2.000  -0.0680   0.02936   0.01946  -0.0073   1.0000   0.9699
  -1.750  -0.0057   0.02811   0.01812  -0.0158   1.0000   0.9885
  -1.500   0.0346   0.02717   0.01714  -0.0206   1.0000   1.0000
  -1.250   0.0335   0.02682   0.01682  -0.0178   1.0000   1.0000
  -1.000   0.0302   0.02652   0.01654  -0.0147   1.0000   1.0000
  -0.750   0.0248   0.02626   0.01631  -0.0113   1.0000   1.0000
  -0.500   0.0176   0.02607   0.01613  -0.0077   1.0000   1.0000
  -0.250   0.0091   0.02595   0.01602  -0.0039   1.0000   1.0000
   0.000   0.0000   0.02591   0.01599   0.0000   1.0000   1.0000
   0.250  -0.0091   0.02595   0.01602   0.0039   1.0000   1.0000
   0.500  -0.0175   0.02606   0.01613   0.0077   1.0000   1.0000
   0.750  -0.0248   0.02626   0.01630   0.0113   1.0000   1.0000
   1.000  -0.0301   0.02651   0.01653   0.0147   1.0000   1.0000
   1.250  -0.0335   0.02681   0.01681   0.0178   1.0000   1.0000
   1.500  -0.0345   0.02716   0.01713   0.0206   1.0000   1.0000
   1.750   0.0056   0.02809   0.01810   0.0158   0.9885   1.0000
   2.000   0.0680   0.02935   0.01946   0.0073   0.9699   1.0000
   2.250   0.1199   0.03019   0.02040   0.0012   0.9482   1.0000
   2.500   0.1894   0.03089   0.02127  -0.0072   0.9209   1.0000
   2.750   0.2664   0.03102   0.02161  -0.0158   0.8903   1.0000
   3.000   0.3505   0.03057   0.02146  -0.0246   0.8618   1.0000
   3.250   0.4862   0.02722   0.01860  -0.0375   0.8165   1.0000
   3.500   0.5366   0.02552   0.01712  -0.0379   0.7816   1.0000
   3.750   0.5699   0.02443   0.01616  -0.0361   0.7472   1.0000
   4.000   0.5966   0.02354   0.01534  -0.0333   0.7087   1.0000
   4.250   0.6174   0.02276   0.01455  -0.0293   0.6602   1.0000
   4.500   0.6323   0.02233   0.01395  -0.0245   0.5997   1.0000
   4.750   0.6419   0.02235   0.01364  -0.0193   0.5202   1.0000
   5.000   0.6409   0.02307   0.01369  -0.0129   0.3987   1.0000
   5.250   0.6416   0.02501   0.01447  -0.0078   0.2926   1.0000
   5.500   0.6607   0.02676   0.01574  -0.0061   0.2488   1.0000
   5.750   0.6840   0.02810   0.01691  -0.0051   0.2267   1.0000
   6.000   0.7080   0.02941   0.01815  -0.0041   0.2118   1.0000
   6.250   0.7335   0.03086   0.01957  -0.0035   0.2022   1.0000
   6.500   0.7568   0.03233   0.02116  -0.0025   0.1952   1.0000
   6.750   0.7821   0.03413   0.02288  -0.0020   0.1900   1.0000
   7.000   0.7980   0.03577   0.02492   0.0001   0.1858   1.0000
   7.250   0.8139   0.03747   0.02689   0.0021   0.1810   1.0000
   7.500   0.8321   0.03931   0.02880   0.0036   0.1768   1.0000
   7.750   0.8497   0.04176   0.03134   0.0050   0.1745   1.0000
   8.000   0.8576   0.04413   0.03412   0.0079   0.1737   1.0000
   8.250   0.8622   0.04668   0.03706   0.0110   0.1729   1.0000
   8.500   0.8626   0.04935   0.04013   0.0144   0.1718   1.0000
   8.750   0.8586   0.05220   0.04333   0.0180   0.1708   1.0000
   9.000   0.8510   0.05531   0.04677   0.0217   0.1704   1.0000
   9.250   0.8407   0.05874   0.05048   0.0251   0.1710   1.0000
   9.500   0.8290   0.06250   0.05444   0.0282   0.1721   1.0000
   9.750   0.8190   0.06648   0.05856   0.0306   0.1734   1.0000
  10.000   0.8112   0.07069   0.06287   0.0325   0.1744   1.0000
  10.250   0.6224   0.08820   0.08037   0.0269   0.1997   1.0000
  10.500   0.5944   0.09846   0.09054   0.0210   0.2194   1.0000
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