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GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 457 AIRFOIL (goe457-il)
Reynolds number: 50,000
Max Cl/Cd: 34.47 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe457-il-50000.txt
Download as CSV file: xf-goe457-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 457 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3875   0.10634   0.09980  -0.0199   1.0000   0.1719
  -7.500  -0.3565   0.09924   0.09261  -0.0176   1.0000   0.1816
  -7.250  -0.3754   0.09916   0.09271  -0.0174   1.0000   0.1859
  -7.000  -0.3653   0.09483   0.08843  -0.0155   1.0000   0.1918
  -6.750  -0.3707   0.09320   0.08690  -0.0155   1.0000   0.1999
  -6.500  -0.3681   0.08995   0.08374  -0.0143   1.0000   0.2064
  -6.250  -0.3756   0.08884   0.08273  -0.0159   1.0000   0.2163
  -6.000  -0.3669   0.08498   0.07892  -0.0126   1.0000   0.2276
  -5.750  -0.3661   0.08225   0.07627  -0.0119   1.0000   0.2377
  -5.500  -0.3666   0.07987   0.07397  -0.0122   1.0000   0.2501
  -5.250  -0.3646   0.07742   0.07157  -0.0122   1.0000   0.2640
  -5.000  -0.3603   0.07460   0.06880  -0.0111   1.0000   0.2792
  -4.750  -0.3550   0.07164   0.06590  -0.0090   1.0000   0.2957
  -4.500  -0.3495   0.06890   0.06320  -0.0069   1.0000   0.3149
  -4.250  -0.3456   0.06629   0.06065  -0.0058   1.0000   0.3400
  -4.000  -0.3418   0.06373   0.05816  -0.0026   1.0000   0.3703
  -3.750  -0.3392   0.06125   0.05577   0.0023   1.0000   0.4068
  -3.500  -0.3390   0.05881   0.05344   0.0078   1.0000   0.4492
  -2.750  -0.3488   0.05193   0.04688   0.0307   1.0000   0.6063
  -2.500  -0.3507   0.04955   0.04461   0.0378   1.0000   0.6527
  -2.250  -0.0980   0.03655   0.02830  -0.0459   1.0000   0.1874
  -2.000  -0.0666   0.03376   0.02495  -0.0470   1.0000   0.1713
  -1.750  -0.0407   0.03173   0.02270  -0.0471   1.0000   0.1668
  -1.500  -0.0147   0.03023   0.02084  -0.0472   1.0000   0.1674
  -1.250   0.0100   0.02899   0.01924  -0.0470   1.0000   0.1681
  -1.000   0.0341   0.02794   0.01791  -0.0467   1.0000   0.1680
  -0.750   0.0555   0.02724   0.01694  -0.0461   1.0000   0.1698
  -0.500   0.0743   0.02682   0.01634  -0.0454   1.0000   0.1730
  -0.250   0.0913   0.02675   0.01625  -0.0449   1.0000   0.1817
   0.000   0.1206   0.02693   0.01635  -0.0468   0.9955   0.1972
   0.250   0.1906   0.02649   0.01599  -0.0547   0.9748   0.2489
   0.500   0.2595   0.02387   0.01503  -0.0616   0.9558   1.0000
   0.750   0.3247   0.02454   0.01523  -0.0690   0.9299   1.0000
   1.000   0.3795   0.02489   0.01531  -0.0742   0.9031   1.0000
   1.250   0.4304   0.02508   0.01532  -0.0783   0.8780   1.0000
   1.500   0.4883   0.02491   0.01502  -0.0830   0.8568   1.0000
   1.750   0.5323   0.02484   0.01485  -0.0853   0.8331   1.0000
   2.000   0.5833   0.02443   0.01438  -0.0883   0.8134   1.0000
   2.250   0.6217   0.02431   0.01421  -0.0892   0.7915   1.0000
   2.500   0.6645   0.02399   0.01385  -0.0905   0.7718   1.0000
   2.750   0.7061   0.02371   0.01351  -0.0916   0.7529   1.0000
   3.000   0.7365   0.02394   0.01373  -0.0913   0.7316   1.0000
   3.250   0.7712   0.02406   0.01380  -0.0914   0.7126   1.0000
   3.500   0.8052   0.02428   0.01395  -0.0915   0.6944   1.0000
   3.750   0.8289   0.02503   0.01475  -0.0905   0.6751   1.0000
   4.000   0.8549   0.02571   0.01544  -0.0898   0.6570   1.0000
   4.250   0.8808   0.02644   0.01618  -0.0891   0.6402   1.0000
   4.500   0.9063   0.02723   0.01699  -0.0883   0.6239   1.0000
   4.750   0.9309   0.02808   0.01793  -0.0874   0.6081   1.0000
   5.000   0.9556   0.02892   0.01880  -0.0865   0.5920   1.0000
   5.250   0.9789   0.02962   0.01953  -0.0850   0.5729   1.0000
   5.500   1.0003   0.03018   0.02011  -0.0830   0.5504   1.0000
   5.750   1.0253   0.03053   0.02044  -0.0812   0.5279   1.0000
   6.000   1.0451   0.03128   0.02126  -0.0793   0.5064   1.0000
   6.250   1.0706   0.03171   0.02166  -0.0778   0.4854   1.0000
   6.500   1.0877   0.03252   0.02261  -0.0756   0.4624   1.0000
   6.750   1.1117   0.03280   0.02288  -0.0738   0.4382   1.0000
   7.000   1.1316   0.03317   0.02329  -0.0715   0.4112   1.0000
   7.250   1.1510   0.03352   0.02361  -0.0691   0.3815   1.0000
   7.500   1.1710   0.03397   0.02395  -0.0668   0.3509   1.0000
   7.750   1.1886   0.03476   0.02471  -0.0644   0.3219   1.0000
   8.000   1.2028   0.03612   0.02619  -0.0621   0.2977   1.0000
   8.250   1.2232   0.03753   0.02759  -0.0606   0.2802   1.0000
   8.500   1.2404   0.03944   0.02968  -0.0590   0.2666   1.0000
   8.750   1.2554   0.04173   0.03223  -0.0573   0.2563   1.0000
   9.000   1.2762   0.04359   0.03419  -0.0563   0.2475   1.0000
   9.250   1.2844   0.04624   0.03725  -0.0541   0.2395   1.0000
   9.500   1.2994   0.04838   0.03958  -0.0527   0.2321   1.0000
   9.750   1.3032   0.05124   0.04282  -0.0503   0.2254   1.0000
  10.000   1.3152   0.05310   0.04485  -0.0486   0.2169   1.0000
  10.250   1.3328   0.05350   0.04527  -0.0470   0.2037   1.0000
  10.500   1.3508   0.05397   0.04580  -0.0454   0.1909   1.0000
  10.750   1.3363   0.05773   0.05007  -0.0419   0.1862   1.0000
  11.000   1.2279   0.07291   0.06586  -0.0377   0.2104   1.0000
  11.250   1.2089   0.07778   0.07081  -0.0367   0.2081   1.0000
  11.500   1.1905   0.08350   0.07660  -0.0368   0.2065   1.0000
  12.000   1.3530   0.06531   0.05753  -0.0285   0.1116   1.0000
  12.250   1.3181   0.06961   0.06230  -0.0251   0.1136   1.0000
  12.500   1.2886   0.07469   0.06768  -0.0238   0.1140   1.0000
  12.750   1.2647   0.08008   0.07325  -0.0238   0.1130   1.0000
  13.000   1.2429   0.08603   0.07933  -0.0249   0.1118   1.0000
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