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GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 439 AIRFOIL (goe439-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.66 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe439-il-1000000-n5.txt
Download as CSV file: xf-goe439-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 439 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2971   0.11261   0.11099  -0.0292   1.0000   0.0050
  -9.750  -0.2930   0.10985   0.10825  -0.0296   1.0000   0.0050
  -9.500  -0.2897   0.10698   0.10539  -0.0300   1.0000   0.0050
  -9.250  -0.2764   0.10288   0.10129  -0.0335   0.9986   0.0050
  -9.000  -0.2660   0.09989   0.09831  -0.0354   0.9925   0.0044
  -8.750  -0.2556   0.09589   0.09432  -0.0384   0.9858   0.0039
  -8.500  -0.2439   0.09132   0.08975  -0.0423   0.9781   0.0036
  -8.250  -0.2298   0.08566   0.08409  -0.0479   0.9690   0.0034
  -8.000  -0.1997   0.08185   0.08025  -0.0553   0.9593   0.0037
  -7.750  -0.1664   0.07609   0.07445  -0.0657   0.9449   0.0037
  -7.500  -0.1372   0.07084   0.06908  -0.0750   0.9125   0.0037
  -7.250  -0.1305   0.06757   0.06564  -0.0776   0.8680   0.0038
  -7.000  -0.1238   0.06481   0.06274  -0.0795   0.8371   0.0042
  -6.750  -0.1172   0.06119   0.05901  -0.0822   0.8129   0.0039
  -6.250  -0.1204   0.01608   0.01226  -0.1128   0.7829   0.0040
  -6.000  -0.0970   0.01407   0.00984  -0.1126   0.7712   0.0041
  -5.750  -0.0722   0.01284   0.00830  -0.1123   0.7604   0.0044
  -5.500  -0.0468   0.01190   0.00709  -0.1120   0.7504   0.0046
  -5.250  -0.0209   0.01121   0.00618  -0.1117   0.7402   0.0048
  -5.000   0.0056   0.01066   0.00545  -0.1114   0.7309   0.0050
  -4.750   0.0317   0.01003   0.00464  -0.1111   0.7219   0.0053
  -4.500   0.0583   0.00956   0.00402  -0.1108   0.7125   0.0057
  -4.250   0.0852   0.00925   0.00361  -0.1106   0.7037   0.0061
  -4.000   0.1119   0.00900   0.00326  -0.1103   0.6941   0.0067
  -3.750   0.1390   0.00879   0.00297  -0.1101   0.6842   0.0074
  -3.500   0.1661   0.00856   0.00263  -0.1098   0.6746   0.0081
  -3.250   0.1929   0.00829   0.00227  -0.1095   0.6642   0.0096
  -3.000   0.2200   0.00812   0.00204  -0.1093   0.6533   0.0110
  -2.750   0.2471   0.00801   0.00184  -0.1091   0.6418   0.0123
  -2.500   0.2740   0.00786   0.00165  -0.1088   0.6292   0.0182
  -2.250   0.3009   0.00778   0.00153  -0.1086   0.6155   0.0244
  -2.000   0.3278   0.00776   0.00145  -0.1083   0.5996   0.0300
  -1.750   0.3547   0.00778   0.00138  -0.1081   0.5836   0.0321
  -1.500   0.3814   0.00774   0.00127  -0.1078   0.5679   0.0363
  -1.250   0.4082   0.00774   0.00121  -0.1076   0.5523   0.0404
  -1.000   0.4350   0.00777   0.00115  -0.1073   0.5377   0.0425
  -0.750   0.4618   0.00776   0.00109  -0.1071   0.5247   0.0497
  -0.500   0.4887   0.00777   0.00106  -0.1069   0.5117   0.0594
  -0.250   0.5154   0.00776   0.00108  -0.1066   0.4997   0.0870
   0.000   0.5422   0.00781   0.00109  -0.1064   0.4878   0.0979
   0.250   0.5693   0.00785   0.00110  -0.1063   0.4766   0.1056
   0.500   0.5962   0.00791   0.00111  -0.1061   0.4649   0.1107
   0.750   0.6228   0.00800   0.00113  -0.1058   0.4502   0.1149
   1.000   0.6492   0.00809   0.00117  -0.1056   0.4339   0.1222
   1.500   0.7026   0.00821   0.00127  -0.1052   0.4120   0.1449
   1.750   0.7291   0.00819   0.00134  -0.1050   0.4025   0.1988
   2.000   0.7547   0.00798   0.00147  -0.1048   0.3930   0.3684
   2.500   0.8126   0.00697   0.00175  -0.1058   0.3732   1.0000
   2.750   0.8389   0.00710   0.00184  -0.1055   0.3643   1.0000
   3.250   0.8912   0.00739   0.00203  -0.1049   0.3454   1.0000
   3.500   0.9173   0.00754   0.00214  -0.1046   0.3375   1.0000
   3.750   0.9435   0.00768   0.00226  -0.1044   0.3295   1.0000
   4.000   0.9695   0.00784   0.00239  -0.1041   0.3209   1.0000
   4.250   0.9948   0.00805   0.00254  -0.1037   0.3067   1.0000
   4.500   1.0195   0.00832   0.00273  -0.1032   0.2867   1.0000
   4.750   1.0450   0.00852   0.00290  -0.1028   0.2765   1.0000
   5.000   1.0695   0.00879   0.00310  -0.1024   0.2589   1.0000
   5.250   1.0922   0.00924   0.00338  -0.1016   0.2274   1.0000
   5.500   1.1134   0.00982   0.00376  -0.1006   0.1876   1.0000
   5.750   1.1267   0.01117   0.00458  -0.0985   0.0934   1.0000
   6.000   1.1490   0.01164   0.00497  -0.0976   0.0752   1.0000
   6.250   1.1675   0.01247   0.00558  -0.0962   0.0294   1.0000
   6.500   1.1903   0.01286   0.00598  -0.0955   0.0197   1.0000
   6.750   1.2129   0.01326   0.00638  -0.0947   0.0124   1.0000
   7.000   1.2351   0.01368   0.00678  -0.0939   0.0092   1.0000
   7.250   1.2575   0.01406   0.00719  -0.0931   0.0076   1.0000
   7.500   1.2795   0.01447   0.00762  -0.0922   0.0065   1.0000
   7.750   1.3000   0.01498   0.00816  -0.0911   0.0054   1.0000
   8.000   1.3214   0.01539   0.00861  -0.0902   0.0049   1.0000
   8.250   1.3421   0.01584   0.00912  -0.0892   0.0044   1.0000
   8.500   1.3619   0.01633   0.00963  -0.0880   0.0038   1.0000
   8.750   1.3791   0.01700   0.01036  -0.0864   0.0035   1.0000
   9.000   1.3971   0.01756   0.01099  -0.0850   0.0033   1.0000
   9.250   1.4141   0.01814   0.01163  -0.0834   0.0031   1.0000
   9.500   1.4291   0.01875   0.01230  -0.0815   0.0029   1.0000
   9.750   1.4416   0.01937   0.01298  -0.0791   0.0027   1.0000
  10.000   1.4528   0.02005   0.01372  -0.0766   0.0026   1.0000
  10.250   1.4628   0.02080   0.01453  -0.0740   0.0024   1.0000
  10.500   1.4701   0.02173   0.01555  -0.0712   0.0023   1.0000
  10.750   1.4755   0.02282   0.01672  -0.0683   0.0022   1.0000
  11.000   1.4799   0.02403   0.01805  -0.0656   0.0021   1.0000
  11.250   1.4844   0.02531   0.01944  -0.0630   0.0020   1.0000
  11.500   1.4886   0.02670   0.02093  -0.0608   0.0020   1.0000
  11.750   1.4975   0.02783   0.02213  -0.0592   0.0018   1.0000
  12.000   1.4966   0.02981   0.02423  -0.0570   0.0018   1.0000
  12.250   1.5000   0.03158   0.02609  -0.0554   0.0017   1.0000
  12.500   1.5006   0.03372   0.02835  -0.0539   0.0017   1.0000
  12.750   1.5018   0.03593   0.03065  -0.0528   0.0016   1.0000
  13.000   1.5022   0.03835   0.03318  -0.0519   0.0016   1.0000
  13.250   1.5020   0.04094   0.03588  -0.0512   0.0015   1.0000
  13.500   1.4998   0.04389   0.03894  -0.0507   0.0015   1.0000
  13.750   1.4939   0.04739   0.04257  -0.0503   0.0015   1.0000
  14.000   1.4943   0.05027   0.04553  -0.0503   0.0014   1.0000
  14.250   1.4926   0.05353   0.04890  -0.0505   0.0014   1.0000
  14.500   1.4852   0.05770   0.05319  -0.0509   0.0014   1.0000
  14.750   1.4808   0.06160   0.05720  -0.0516   0.0013   1.0000
  15.000   1.4763   0.06566   0.06137  -0.0524   0.0013   1.0000
  15.250   1.4711   0.06996   0.06581  -0.0535   0.0013   1.0000
  15.500   1.4607   0.07514   0.07112  -0.0548   0.0013   1.0000
  15.750   1.4556   0.07969   0.07578  -0.0562   0.0013   1.0000
  16.000   1.4497   0.08447   0.08066  -0.0578   0.0013   1.0000
  16.250   1.4406   0.08987   0.08618  -0.0597   0.0012   1.0000
  16.500   1.4336   0.09502   0.09145  -0.0616   0.0012   1.0000
  16.750   1.4223   0.10106   0.09762  -0.0639   0.0012   1.0000
  17.000   1.4113   0.10715   0.10385  -0.0664   0.0012   1.0000
  17.250   1.4016   0.11315   0.10998  -0.0690   0.0012   1.0000
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