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GOE 443 AIRFOIL (goe443-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 443 AIRFOIL (goe443-il)
Reynolds number: 1,000,000
Max Cl/Cd: 43.28 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe443-il-1000000.txt
Download as CSV file: xf-goe443-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 443 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6353   0.08425   0.08265   0.0024   1.0000   0.0070
  -8.000  -0.6408   0.07973   0.07816  -0.0016   1.0000   0.0070
  -7.750  -0.6429   0.07500   0.07341  -0.0055   1.0000   0.0070
  -7.500  -0.6396   0.07021   0.06857  -0.0086   1.0000   0.0070
  -7.250  -0.6339   0.06567   0.06396  -0.0107   1.0000   0.0071
  -7.000  -0.6269   0.06120   0.05940  -0.0120   1.0000   0.0071
  -6.750  -0.6179   0.05688   0.05497  -0.0128   1.0000   0.0071
  -6.500  -0.6073   0.05263   0.05059  -0.0131   1.0000   0.0072
  -6.250  -0.5952   0.04843   0.04625  -0.0130   1.0000   0.0072
  -6.000  -0.5818   0.04440   0.04205  -0.0125   1.0000   0.0072
  -5.750  -0.5674   0.04043   0.03789  -0.0116   1.0000   0.0072
  -5.500  -0.5520   0.03666   0.03391  -0.0104   1.0000   0.0072
  -5.250  -0.5360   0.03296   0.02998  -0.0090   1.0000   0.0072
  -5.000  -0.5195   0.02942   0.02619  -0.0073   1.0000   0.0073
  -4.750  -0.5122   0.02179   0.01795  -0.0040   1.0000   0.0060
  -4.500  -0.4949   0.01659   0.01217  -0.0008   1.0000   0.0053
  -4.250  -0.4724   0.01469   0.01003   0.0008   1.0000   0.0063
  -4.000  -0.4471   0.01505   0.01037   0.0014   1.0000   0.0075
  -3.750  -0.4273   0.01182   0.00678   0.0033   1.0000   0.0081
  -3.500  -0.4048   0.01095   0.00582   0.0043   1.0000   0.0100
  -3.250  -0.3840   0.00940   0.00410   0.0061   1.0000   0.0091
  -3.000  -0.3622   0.00856   0.00315   0.0076   1.0000   0.0090
  -2.750  -0.3399   0.00784   0.00232   0.0089   1.0000   0.0101
  -2.500  -0.3163   0.00750   0.00194   0.0098   1.0000   0.0132
  -2.250  -0.2924   0.00729   0.00170   0.0107   1.0000   0.0151
  -2.000  -0.2692   0.00689   0.00131   0.0117   1.0000   0.0350
  -1.750  -0.2427   0.00670   0.00114   0.0119   0.9996   0.0522
  -1.500  -0.2101   0.00602   0.00097   0.0103   0.9974   0.2034
  -1.250  -0.1812   0.00479   0.00085   0.0091   0.9946   0.5222
  -1.000  -0.1528   0.00412   0.00081   0.0087   0.9908   0.7037
  -0.750  -0.1234   0.00371   0.00081   0.0084   0.9864   0.8151
  -0.500  -0.0914   0.00346   0.00082   0.0076   0.9831   0.8863
  -0.250  -0.0489   0.00344   0.00097   0.0047   0.9837   0.9631
   0.000  -0.0001   0.00354   0.00108   0.0000   0.9851   0.9851
   0.250   0.0489   0.00344   0.00097  -0.0047   0.9636   0.9838
   0.500   0.0914   0.00346   0.00082  -0.0076   0.8863   0.9831
   0.750   0.1235   0.00371   0.00081  -0.0084   0.8160   0.9865
   1.000   0.1537   0.00405   0.00082  -0.0089   0.7230   0.9908
   1.250   0.1813   0.00479   0.00084  -0.0092   0.5220   0.9947
   1.500   0.2105   0.00597   0.00096  -0.0104   0.2164   0.9975
   1.750   0.2429   0.00670   0.00113  -0.0119   0.0519   0.9997
   2.000   0.2686   0.00688   0.00131  -0.0116   0.0357   1.0000
   2.250   0.2918   0.00728   0.00169  -0.0105   0.0151   1.0000
   2.500   0.3157   0.00750   0.00194  -0.0097   0.0134   1.0000
   2.750   0.3393   0.00784   0.00232  -0.0087   0.0100   1.0000
   3.000   0.3615   0.00854   0.00314  -0.0074   0.0090   1.0000
   3.250   0.3833   0.00938   0.00409  -0.0060   0.0091   1.0000
   3.500   0.4042   0.01091   0.00578  -0.0042   0.0100   1.0000
   3.750   0.4268   0.01173   0.00668  -0.0032   0.0081   1.0000
   4.000   0.4467   0.01484   0.01013  -0.0013   0.0075   1.0000
   4.250   0.4715   0.01478   0.01013  -0.0006   0.0064   1.0000
   4.500   0.4943   0.01655   0.01213   0.0009   0.0053   1.0000
   4.750   0.5118   0.02176   0.01792   0.0041   0.0060   1.0000
  15.500   0.7548   0.19955   0.19781  -0.0540   0.0031   1.0000
  15.750   0.7620   0.20332   0.20156  -0.0559   0.0030   1.0000
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