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GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 6K AIRFOIL (goe06k-il)
Reynolds number: 50,000
Max Cl/Cd: 26.39 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe06k-il-50000.txt
Download as CSV file: xf-goe06k-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 6K 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4986   0.10723   0.10072  -0.0244   1.0000   0.1835
  -7.750  -0.4846   0.10261   0.09610  -0.0222   1.0000   0.1951
  -7.500  -0.5128   0.10218   0.09584  -0.0211   1.0000   0.1974
  -7.250  -0.5046   0.09826   0.09195  -0.0183   1.0000   0.2096
  -7.000  -0.5070   0.09531   0.08907  -0.0162   1.0000   0.2221
  -6.750  -0.5108   0.09255   0.08639  -0.0142   1.0000   0.2341
  -6.500  -0.5160   0.08994   0.08386  -0.0122   1.0000   0.2488
  -6.250  -0.5215   0.08733   0.08132  -0.0104   1.0000   0.2642
  -6.000  -0.5329   0.08521   0.07927  -0.0095   1.0000   0.2815
  -5.750  -0.5265   0.08190   0.07597  -0.0049   1.0000   0.3059
  -5.500  -0.5274   0.07912   0.07325  -0.0014   1.0000   0.3321
  -5.250  -0.5301   0.07660   0.07079   0.0024   1.0000   0.3633
  -5.000  -0.5298   0.07391   0.06817   0.0075   1.0000   0.3993
  -4.500  -0.2246   0.05538   0.04875   0.0021   1.0000   0.8932
  -4.250  -0.2605   0.05525   0.04881   0.0100   1.0000   0.8629
  -4.000  -0.3047   0.05516   0.04893   0.0185   1.0000   0.8234
  -3.750  -0.3498   0.05489   0.04887   0.0266   1.0000   0.7920
  -3.500  -0.3956   0.05426   0.04845   0.0344   1.0000   0.7638
  -3.250  -0.4000   0.04435   0.03655  -0.0235   1.0000   0.2286
  -3.000  -0.3611   0.04019   0.03127  -0.0255   1.0000   0.1680
  -2.750  -0.3349   0.03722   0.02772  -0.0248   1.0000   0.1522
  -2.500  -0.3083   0.03474   0.02455  -0.0237   1.0000   0.1391
  -2.250  -0.2832   0.03253   0.02178  -0.0225   1.0000   0.1329
  -2.000  -0.2579   0.03075   0.01948  -0.0212   1.0000   0.1314
  -1.750  -0.2340   0.02939   0.01780  -0.0201   1.0000   0.1398
  -1.500  -0.2067   0.02791   0.01602  -0.0194   1.0000   0.1447
  -1.250  -0.1785   0.02674   0.01465  -0.0188   1.0000   0.1529
  -1.000  -0.1484   0.02574   0.01360  -0.0189   1.0000   0.1780
  -0.750  -0.1205   0.02483   0.01265  -0.0185   1.0000   0.2063
  -0.500  -0.0510   0.02157   0.01153  -0.0253   1.0000   1.0000
  -0.250  -0.0306   0.02183   0.01131  -0.0241   1.0000   1.0000
   0.000  -0.0104   0.02210   0.01125  -0.0231   1.0000   1.0000
   0.250   0.0097   0.02240   0.01127  -0.0221   1.0000   1.0000
   0.500   0.0297   0.02272   0.01133  -0.0211   1.0000   1.0000
   0.750   0.0496   0.02306   0.01147  -0.0202   1.0000   1.0000
   1.000   0.0695   0.02343   0.01168  -0.0193   1.0000   1.0000
   1.250   0.0893   0.02381   0.01193  -0.0185   1.0000   1.0000
   1.500   0.1090   0.02422   0.01223  -0.0177   1.0000   1.0000
   1.750   0.1286   0.02465   0.01257  -0.0169   1.0000   1.0000
   2.000   0.1480   0.02511   0.01297  -0.0161   1.0000   1.0000
   2.250   0.1673   0.02560   0.01342  -0.0153   1.0000   1.0000
   2.500   0.1865   0.02612   0.01392  -0.0146   1.0000   1.0000
   2.750   0.2054   0.02667   0.01447  -0.0139   1.0000   1.0000
   3.000   0.2241   0.02725   0.01509  -0.0132   1.0000   1.0000
   3.250   0.2426   0.02787   0.01575  -0.0126   1.0000   1.0000
   3.500   0.2607   0.02854   0.01648  -0.0119   1.0000   1.0000
   3.750   0.2786   0.02925   0.01727  -0.0114   1.0000   1.0000
   4.000   0.2960   0.03001   0.01813  -0.0108   1.0000   1.0000
   4.250   0.3130   0.03084   0.01912  -0.0103   1.0000   1.0000
   4.500   0.3295   0.03173   0.02014  -0.0098   1.0000   1.0000
   4.750   0.3453   0.03270   0.02127  -0.0094   1.0000   1.0000
   5.000   0.3607   0.03375   0.02249  -0.0090   1.0000   1.0000
   5.250   0.3752   0.03491   0.02382  -0.0087   1.0000   1.0000
   5.500   0.4097   0.03681   0.02605  -0.0128   0.9890   1.0000
   5.750   0.7398   0.02803   0.01572  -0.0370   0.1644   1.0000
   6.000   0.8395   0.03235   0.01995  -0.0482   0.1184   1.0000
   6.250   0.9036   0.03693   0.02469  -0.0538   0.1096   1.0000
   6.500   0.9288   0.03943   0.02785  -0.0521   0.1053   1.0000
   6.750   0.9518   0.04241   0.03130  -0.0504   0.1016   1.0000
   7.000   0.9720   0.04602   0.03547  -0.0482   0.1041   1.0000
   7.250   0.9886   0.05000   0.03988  -0.0457   0.1075   1.0000
   7.500   0.9970   0.05341   0.04403  -0.0415   0.1144   1.0000
   7.750   1.0107   0.05852   0.04943  -0.0394   0.1222   1.0000
   8.000   1.0129   0.06282   0.05436  -0.0352   0.1354   1.0000
   8.250   0.9990   0.06671   0.05908  -0.0299   0.1563   1.0000
   8.500   0.9843   0.07227   0.06518  -0.0267   0.1858   1.0000
   8.750   0.9554   0.07811   0.07142  -0.0249   0.2226   1.0000
   9.000   0.9190   0.08262   0.07602  -0.0227   0.2374   1.0000
   9.250   0.8788   0.08816   0.08154  -0.0231   0.2516   1.0000
   9.500   0.8280   0.09727   0.09051  -0.0306   0.2821   1.0000
   9.750   0.7517   0.08785   0.08146  -0.0113   0.1967   1.0000
  10.000   0.7526   0.11481   0.10770  -0.0485   0.4016   1.0000
  10.250   0.7666   0.11944   0.11233  -0.0475   0.3835   1.0000
  10.500   0.7582   0.12219   0.11503  -0.0466   0.3621   1.0000
  10.750   0.7634   0.12608   0.11892  -0.0460   0.3469   1.0000
  11.000   0.6314   0.12559   0.11888  -0.0352   0.3416   1.0000
  11.250   0.6283   0.12864   0.12192  -0.0349   0.3267   1.0000
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