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GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 5K AIRFOIL (goe05k-il)
Reynolds number: 1,000,000
Max Cl/Cd: 95.1 at α=0.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe05k-il-1000000-n5.txt
Download as CSV file: xf-goe05k-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 5K 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5247   0.08940   0.08782  -0.0098   1.0000   0.0017
  -7.500  -0.5285   0.08682   0.08527  -0.0096   1.0000   0.0017
  -7.250  -0.5279   0.08351   0.08198  -0.0112   1.0000   0.0017
  -7.000  -0.5237   0.07993   0.07840  -0.0137   1.0000   0.0017
  -6.750  -0.5176   0.07615   0.07462  -0.0163   1.0000   0.0017
  -6.500  -0.5098   0.07235   0.07081  -0.0187   1.0000   0.0017
  -6.250  -0.5006   0.06847   0.06691  -0.0210   1.0000   0.0017
  -6.000  -0.4773   0.06334   0.06171  -0.0265   0.9990   0.0017
  -5.750  -0.4498   0.05808   0.05637  -0.0323   0.9975   0.0018
  -5.500  -0.4205   0.05293   0.05112  -0.0374   0.9960   0.0018
  -5.250  -0.3956   0.04781   0.04589  -0.0415   0.9942   0.0018
  -2.750  -0.1054   0.01329   0.00897  -0.0509   0.9738   0.0016
  -2.500  -0.0764   0.01118   0.00658  -0.0505   0.9719   0.0014
  -2.250  -0.0472   0.00924   0.00436  -0.0501   0.9705   0.0013
  -2.000  -0.0185   0.00775   0.00263  -0.0499   0.9692   0.0015
  -1.750   0.0110   0.00726   0.00203  -0.0503   0.9676   0.0028
  -1.500   0.0345   0.00671   0.00137  -0.0492   0.9622   0.0033
  -1.250   0.0640   0.00640   0.00101  -0.0496   0.9594   0.0064
  -1.000   0.0944   0.00604   0.00076  -0.0504   0.9572   0.0588
  -0.750   0.1188   0.00497   0.00066  -0.0504   0.9529   0.4085
  -0.500   0.1388   0.00395   0.00063  -0.0491   0.9461   0.7378
   0.000   0.2367   0.00334   0.00059  -0.0589   0.9341   0.9785
   0.250   0.2943   0.00336   0.00055  -0.0659   0.9125   0.9981
   0.500   0.3288   0.00346   0.00050  -0.0674   0.8702   1.0000
   0.750   0.3490   0.00367   0.00049  -0.0655   0.8053   1.0000
   1.000   0.3663   0.00403   0.00056  -0.0631   0.7217   1.0000
   1.250   0.3683   0.00569   0.00082  -0.0580   0.3474   1.0000
   1.500   0.3803   0.00714   0.00115  -0.0552   0.0204   1.0000
   1.750   0.4034   0.00747   0.00146  -0.0542   0.0043   1.0000
   2.000   0.4262   0.00785   0.00192  -0.0530   0.0021   1.0000
   2.250   0.4484   0.00839   0.00256  -0.0516   0.0018   1.0000
   2.500   0.4692   0.00916   0.00345  -0.0499   0.0018   1.0000
   2.750   0.4895   0.01021   0.00464  -0.0480   0.0018   1.0000
   3.000   0.5106   0.01175   0.00634  -0.0461   0.0020   1.0000
   3.250   0.5355   0.01375   0.00856  -0.0442   0.0028   1.0000
   3.500   0.5593   0.01505   0.01005  -0.0430   0.0014   1.0000
   4.000   0.6042   0.01995   0.01552  -0.0390   0.0010   1.0000
   4.500   0.6458   0.02644   0.02264  -0.0334   0.0014   1.0000
   4.750   0.6645   0.02964   0.02612  -0.0308   0.0015   1.0000
   5.000   0.6823   0.03293   0.02967  -0.0284   0.0014   1.0000
   5.250   0.6991   0.03635   0.03332  -0.0262   0.0013   1.0000
   5.500   0.7150   0.03995   0.03714  -0.0241   0.0013   1.0000
   5.750   0.7290   0.04364   0.04103  -0.0224   0.0012   1.0000
   6.000   0.7417   0.04741   0.04498  -0.0209   0.0012   1.0000
   6.250   0.7512   0.05133   0.04906  -0.0197   0.0011   1.0000
   6.500   0.7586   0.05605   0.05394  -0.0185   0.0011   1.0000
   6.750   0.7674   0.06040   0.05842  -0.0178   0.0011   1.0000
   7.000   0.7745   0.06466   0.06280  -0.0174   0.0011   1.0000
   7.250   0.7795   0.06908   0.06731  -0.0173   0.0011   1.0000
   7.500   0.7820   0.07369   0.07201  -0.0178   0.0011   1.0000
   7.750   0.7828   0.07801   0.07638  -0.0186   0.0011   1.0000
   8.000   0.7800   0.08251   0.08093  -0.0199   0.0011   1.0000
   8.250   0.7715   0.08649   0.08493  -0.0209   0.0011   1.0000
   8.500   0.7639   0.09128   0.08972  -0.0253   0.0011   1.0000
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