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GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 441 AIRFOIL (goe441-il)
Reynolds number: 50,000
Max Cl/Cd: 31 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe441-il-50000-n5.txt
Download as CSV file: xf-goe441-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250   0.0369   0.11190   0.10501  -0.0890   0.8936   0.1350
  -8.000   0.0435   0.10965   0.10275  -0.0934   0.8863   0.1359
  -7.750   0.0405   0.10809   0.10124  -0.0935   0.8732   0.1361
  -7.500   0.0728   0.10277   0.09588  -0.0955   0.8689   0.1376
  -7.250   0.0864   0.10006   0.09319  -0.0945   0.8574   0.1406
  -6.250   0.0988   0.08661   0.07962  -0.1016   0.8146   0.0964
  -6.000   0.1028   0.08427   0.07729  -0.1013   0.8011   0.0943
  -5.750   0.1114   0.08088   0.07387  -0.1039   0.7905   0.0918
  -5.500   0.1174   0.07559   0.06850  -0.1113   0.7789   0.0881
  -5.250   0.1272   0.07251   0.06539  -0.1137   0.7656   0.0879
  -5.000   0.1541   0.06758   0.06034  -0.1209   0.7581   0.0887
  -4.750   0.1659   0.06580   0.05855  -0.1209   0.7440   0.0900
  -4.500   0.1928   0.06146   0.05408  -0.1272   0.7342   0.0908
  -4.250   0.2252   0.05552   0.04788  -0.1369   0.7232   0.0908
  -4.000   0.2635   0.05028   0.04229  -0.1460   0.7129   0.0921
  -3.750   0.3204   0.04373   0.03496  -0.1596   0.7037   0.0972
  -3.500   0.3575   0.04112   0.03200  -0.1639   0.6932   0.1005
  -3.250   0.3960   0.03903   0.02956  -0.1675   0.6838   0.1050
  -3.000   0.4339   0.03694   0.02695  -0.1712   0.6733   0.1116
  -2.750   0.4685   0.03577   0.02557  -0.1730   0.6647   0.1179
  -2.500   0.4997   0.03476   0.02426  -0.1744   0.6545   0.1256
  -2.250   0.5352   0.03374   0.02287  -0.1761   0.6465   0.1357
  -2.000   0.5612   0.03344   0.02258  -0.1762   0.6374   0.1438
  -1.750   0.5930   0.03288   0.02183  -0.1771   0.6297   0.1551
  -1.500   0.6238   0.03250   0.02125  -0.1778   0.6224   0.1679
  -1.250   0.6524   0.03232   0.02088  -0.1782   0.6146   0.1814
  -1.000   0.6874   0.03182   0.02016  -0.1792   0.6092   0.1972
  -0.750   0.7104   0.03196   0.02033  -0.1789   0.6010   0.2102
  -0.500   0.7417   0.03170   0.01993  -0.1795   0.5952   0.2264
  -0.250   0.7742   0.03143   0.01953  -0.1802   0.5900   0.2453
   0.000   0.7983   0.03166   0.01979  -0.1800   0.5832   0.2642
   0.250   0.8295   0.03153   0.01964  -0.1806   0.5779   0.2936
   0.500   0.8638   0.03129   0.01945  -0.1814   0.5736   0.3346
   0.750   0.8836   0.03191   0.02027  -0.1806   0.5669   0.3806
   1.000   0.9108   0.03216   0.02059  -0.1805   0.5618   0.4427
   1.250   0.9422   0.03219   0.02059  -0.1807   0.5577   0.5080
   1.750   0.9808   0.03322   0.02197  -0.1780   0.5472   0.6335
   2.000   1.0019   0.03333   0.02224  -0.1765   0.5427   0.7129
   2.250   1.0211   0.03295   0.02204  -0.1741   0.5392   0.8425
   2.500   1.0435   0.03379   0.02272  -0.1739   0.5343   1.0000
   2.750   1.0608   0.03504   0.02389  -0.1732   0.5287   1.0000
   3.000   1.0873   0.03577   0.02443  -0.1734   0.5241   1.0000
   3.250   1.1205   0.03615   0.02456  -0.1743   0.5204   1.0000
   3.500   1.1446   0.03704   0.02531  -0.1741   0.5163   1.0000
   3.750   1.1467   0.03905   0.02742  -0.1715   0.5102   1.0000
   4.000   1.1654   0.04017   0.02847  -0.1708   0.5055   1.0000
   4.250   1.1954   0.04067   0.02881  -0.1711   0.5018   1.0000
   4.500   1.2327   0.04084   0.02878  -0.1724   0.4989   1.0000
   4.750   1.2044   0.04457   0.03280  -0.1666   0.4914   1.0000
   5.000   1.2028   0.04679   0.03506  -0.1637   0.4858   1.0000
   5.250   1.2297   0.04740   0.03557  -0.1637   0.4823   1.0000
   5.500   1.2708   0.04729   0.03531  -0.1651   0.4796   1.0000
   5.750   1.1550   0.05829   0.04684  -0.1543   0.4654   1.0000
   6.000   1.1799   0.05886   0.04733  -0.1539   0.4623   1.0000
   6.250   1.2168   0.05837   0.04673  -0.1541   0.4602   1.0000
   8.750   1.0872   0.10779   0.09684  -0.1461   0.3867   1.0000
   9.000   1.0530   0.11594   0.10511  -0.1469   0.3761   1.0000
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