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GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 441 AIRFOIL (goe441-il)
Reynolds number: 200,000
Max Cl/Cd: 67.03 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe441-il-200000.txt
Download as CSV file: xf-goe441-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 441 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000   0.1197   0.09487   0.09107  -0.1081   0.9047   0.0707
  -8.750   0.1278   0.09263   0.08883  -0.1086   0.8944   0.0723
  -8.500   0.1201   0.09059   0.08675  -0.1135   0.8846   0.0754
  -8.250   0.1209   0.08743   0.08359  -0.1157   0.8739   0.0760
  -8.000   0.1400   0.08466   0.08077  -0.1138   0.8675   0.0766
  -7.750   0.1542   0.08249   0.07860  -0.1129   0.8577   0.0774
  -7.500   0.1668   0.08032   0.07637  -0.1130   0.8499   0.0788
  -7.250   0.1757   0.07825   0.07431  -0.1136   0.8391   0.0811
  -7.000   0.1606   0.07479   0.07083  -0.1243   0.8281   0.0848
  -6.750   0.1760   0.07251   0.06853  -0.1206   0.8184   0.0854
  -6.500   0.1919   0.07049   0.06646  -0.1190   0.8088   0.0863
  -6.250   0.2061   0.06850   0.06442  -0.1188   0.7978   0.0876
  -6.000   0.2191   0.06636   0.06226  -0.1200   0.7858   0.0895
  -5.500   0.2738   0.03870   0.03393  -0.1715   0.7660   0.0759
  -5.250   0.2969   0.03699   0.03216  -0.1720   0.7532   0.0765
  -5.000   0.3483   0.02452   0.01833  -0.1895   0.7414   0.0694
  -4.750   0.3785   0.02290   0.01640  -0.1909   0.7248   0.0703
  -4.500   0.4089   0.02148   0.01463  -0.1921   0.7067   0.0718
  -4.250   0.4395   0.02029   0.01300  -0.1931   0.6871   0.0744
  -4.000   0.4688   0.01934   0.01174  -0.1936   0.6669   0.0769
  -3.750   0.4962   0.01895   0.01120  -0.1936   0.6475   0.0794
  -3.500   0.5250   0.01841   0.01037  -0.1938   0.6298   0.0827
  -3.250   0.5537   0.01786   0.00961  -0.1940   0.6145   0.0865
  -3.000   0.5817   0.01772   0.00934  -0.1941   0.6016   0.0917
  -2.750   0.6102   0.01740   0.00884  -0.1943   0.5909   0.0979
  -2.500   0.6390   0.01728   0.00853  -0.1944   0.5811   0.1056
  -2.250   0.6677   0.01699   0.00819  -0.1947   0.5733   0.1148
  -2.000   0.6968   0.01675   0.00790  -0.1951   0.5659   0.1253
  -1.750   0.7262   0.01667   0.00769  -0.1955   0.5596   0.1369
  -1.500   0.7553   0.01675   0.00769  -0.1957   0.5537   0.1482
  -1.250   0.7839   0.01674   0.00772  -0.1960   0.5476   0.1594
  -1.000   0.8131   0.01683   0.00773  -0.1962   0.5421   0.1703
  -0.750   0.8426   0.01705   0.00782  -0.1965   0.5372   0.1815
  -0.500   0.8710   0.01705   0.00790  -0.1967   0.5324   0.1932
  -0.250   0.9000   0.01709   0.00795  -0.1970   0.5278   0.2067
   0.000   0.9297   0.01716   0.00801  -0.1975   0.5235   0.2250
   0.250   0.9604   0.01728   0.00813  -0.1982   0.5192   0.2566
   0.500   0.9890   0.01717   0.00833  -0.1986   0.5150   0.3166
   0.750   1.0174   0.01725   0.00868  -0.1988   0.5108   0.4070
   1.000   1.0457   0.01748   0.00897  -0.1988   0.5070   0.4726
   1.250   1.0743   0.01778   0.00925  -0.1990   0.5033   0.5164
   1.500   1.1027   0.01814   0.00961  -0.1991   0.4996   0.5521
   1.750   1.1284   0.01828   0.00990  -0.1987   0.4958   0.5840
   2.000   1.1549   0.01847   0.01019  -0.1985   0.4921   0.6182
   2.250   1.1816   0.01866   0.01046  -0.1983   0.4885   0.6576
   2.500   1.2087   0.01887   0.01072  -0.1981   0.4851   0.7055
   2.750   1.2359   0.01920   0.01107  -0.1979   0.4817   0.7696
   3.000   1.2536   0.01905   0.01121  -0.1957   0.4787   1.0000
   3.250   1.2800   0.01937   0.01151  -0.1956   0.4750   1.0000
   3.500   1.3070   0.01970   0.01178  -0.1956   0.4713   1.0000
   3.750   1.3347   0.02003   0.01203  -0.1957   0.4678   1.0000
   4.000   1.3636   0.02042   0.01230  -0.1961   0.4647   1.0000
   4.250   1.3918   0.02097   0.01276  -0.1963   0.4615   1.0000
   4.500   1.4147   0.02128   0.01315  -0.1956   0.4579   1.0000
   4.750   1.4391   0.02162   0.01351  -0.1951   0.4542   1.0000
   5.000   1.4648   0.02194   0.01382  -0.1949   0.4507   1.0000
   5.250   1.4920   0.02226   0.01408  -0.1949   0.4476   1.0000
   5.500   1.5211   0.02271   0.01442  -0.1953   0.4446   1.0000
   5.750   1.5444   0.02320   0.01496  -0.1948   0.4415   1.0000
   6.000   1.5655   0.02359   0.01545  -0.1938   0.4378   1.0000
   6.250   1.5886   0.02395   0.01584  -0.1931   0.4342   1.0000
   6.500   1.6136   0.02426   0.01613  -0.1928   0.4309   1.0000
   6.750   1.6410   0.02459   0.01640  -0.1929   0.4280   1.0000
   7.000   1.6698   0.02515   0.01689  -0.1933   0.4251   1.0000
   7.250   1.6864   0.02563   0.01754  -0.1916   0.4218   1.0000
   7.500   1.7055   0.02609   0.01811  -0.1904   0.4181   1.0000
   7.750   1.7274   0.02645   0.01851  -0.1896   0.4146   1.0000
   8.000   1.7525   0.02674   0.01876  -0.1893   0.4115   1.0000
   8.250   1.7814   0.02708   0.01903  -0.1897   0.4086   1.0000
   8.500   1.7984   0.02770   0.01977  -0.1882   0.4052   1.0000
   8.750   1.8122   0.02829   0.02051  -0.1861   0.4015   1.0000
   9.000   1.8304   0.02876   0.02104  -0.1848   0.3980   1.0000
   9.250   1.8528   0.02910   0.02140  -0.1841   0.3949   1.0000
   9.500   1.8805   0.02937   0.02161  -0.1843   0.3920   1.0000
   9.750   1.8961   0.02997   0.02230  -0.1826   0.3882   1.0000
  10.000   1.9000   0.03059   0.02309  -0.1790   0.3837   1.0000
  10.250   1.9121   0.03083   0.02337  -0.1766   0.3793   1.0000
  10.500   1.9352   0.03079   0.02324  -0.1758   0.3752   1.0000
  10.750   1.9413   0.03144   0.02398  -0.1727   0.3711   1.0000
  11.000   1.9384   0.03232   0.02503  -0.1683   0.3667   1.0000
  11.250   1.9470   0.03285   0.02561  -0.1657   0.3625   1.0000
  11.500   1.9662   0.03306   0.02578  -0.1646   0.3587   1.0000
  11.750   1.9720   0.03396   0.02676  -0.1619   0.3546   1.0000
  12.000   1.9662   0.03531   0.02830  -0.1579   0.3502   1.0000
  12.250   1.9723   0.03614   0.02919  -0.1555   0.3457   1.0000
  12.500   1.9907   0.03643   0.02941  -0.1544   0.3415   1.0000
  12.750   1.9844   0.03818   0.03134  -0.1510   0.3371   1.0000
  13.000   1.9798   0.03989   0.03320  -0.1480   0.3323   1.0000
  13.250   1.9861   0.04094   0.03427  -0.1461   0.3276   1.0000
  13.500   1.9918   0.04217   0.03553  -0.1442   0.3228   1.0000
  13.750   1.9794   0.04482   0.03839  -0.1412   0.3175   1.0000
  14.000   1.9797   0.04655   0.04017  -0.1394   0.3123   1.0000
  14.250   1.9826   0.04821   0.04185  -0.1377   0.3071   1.0000
  14.500   1.9682   0.05161   0.04545  -0.1355   0.3015   1.0000
  14.750   1.9682   0.05374   0.04761  -0.1341   0.2959   1.0000
  15.000   1.9629   0.05659   0.05056  -0.1327   0.2905   1.0000
  15.250   1.9492   0.06054   0.05469  -0.1313   0.2849   1.0000
  15.500   1.9521   0.06256   0.05664  -0.1304   0.2784   1.0000
  15.750   1.9304   0.06785   0.06216  -0.1294   0.2727   1.0000
  16.000   1.9199   0.07185   0.06624  -0.1288   0.2664   1.0000
  16.250   1.9082   0.07614   0.07062  -0.1283   0.2602   1.0000
  16.500   1.8880   0.08179   0.07641  -0.1282   0.2538   1.0000
  16.750   1.8784   0.08597   0.08061  -0.1281   0.2467   1.0000
  17.000   1.8536   0.09256   0.08739  -0.1285   0.2403   1.0000
  17.250   1.8423   0.09714   0.09196  -0.1288   0.2325   1.0000
  17.500   1.8166   0.10402   0.09901  -0.1297   0.2257   1.0000
  17.750   1.7996   0.10956   0.10458  -0.1304   0.2167   1.0000
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