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GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il)
Reynolds number: 500,000
Max Cl/Cd: 110.46 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe610bm-il-500000.txt
Download as CSV file: xf-goe610bm-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610-B MOD. AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3001   0.09570   0.09360  -0.0248   1.0000   0.0154
  -7.500  -0.2945   0.09287   0.09081  -0.0261   1.0000   0.0160
  -7.250  -0.2965   0.09080   0.08879  -0.0257   1.0000   0.0166
  -7.000  -0.2700   0.08656   0.08455  -0.0377   0.9906   0.0176
  -6.750  -0.2403   0.08160   0.07957  -0.0473   0.9835   0.0177
  -6.500  -0.2144   0.07695   0.07490  -0.0544   0.9739   0.0178
  -6.250  -0.1891   0.07234   0.07025  -0.0609   0.9633   0.0178
  -6.000  -0.1768   0.06669   0.06458  -0.0641   0.9521   0.0182
  -5.750  -0.1632   0.06391   0.06176  -0.0645   0.9405   0.0185
  -5.500  -0.1456   0.06101   0.05881  -0.0665   0.9286   0.0190
  -5.250  -0.1238   0.05782   0.05556  -0.0699   0.9172   0.0197
  -5.000  -0.0974   0.05420   0.05186  -0.0746   0.9067   0.0211
  -4.750  -0.0485   0.04932   0.04677  -0.0847   0.8972   0.0236
  -4.500  -0.0133   0.04493   0.04220  -0.0898   0.8869   0.0238
  -4.250   0.0204   0.04017   0.03723  -0.0942   0.8772   0.0239
  -4.000   0.0438   0.03421   0.03110  -0.0982   0.8680   0.0252
  -3.750   0.0700   0.03236   0.02915  -0.0995   0.8574   0.0264
  -3.500   0.1012   0.02984   0.02644  -0.1015   0.8470   0.0291
  -3.250   0.1406   0.02811   0.02425  -0.1027   0.8371   0.0326
  -3.000   0.1736   0.02182   0.01750  -0.1064   0.8278   0.0347
  -1.250   0.3851   0.01271   0.00648  -0.1098   0.7501   0.0466
  -1.000   0.4139   0.01268   0.00631  -0.1096   0.7381   0.0449
  -0.750   0.4432   0.01162   0.00511  -0.1098   0.7265   0.0435
  -0.500   0.4722   0.01108   0.00447  -0.1100   0.7137   0.0434
  -0.250   0.5009   0.01084   0.00413  -0.1100   0.6999   0.0441
   0.000   0.5298   0.01041   0.00363  -0.1101   0.6849   0.0441
   0.250   0.5585   0.01012   0.00326  -0.1102   0.6684   0.0444
   0.500   0.5875   0.00977   0.00285  -0.1104   0.6484   0.0454
   0.750   0.6162   0.00958   0.00255  -0.1106   0.6258   0.0474
   1.000   0.6447   0.00954   0.00240  -0.1107   0.6020   0.0495
   1.250   0.6729   0.00958   0.00232  -0.1108   0.5817   0.0524
   1.500   0.7010   0.00965   0.00230  -0.1109   0.5651   0.0571
   1.750   0.7299   0.00944   0.00237  -0.1113   0.5520   0.2116
   2.250   0.7799   0.00809   0.00257  -0.1105   0.5318   1.0000
   2.500   0.8079   0.00827   0.00267  -0.1105   0.5216   1.0000
   2.750   0.8357   0.00848   0.00277  -0.1106   0.5110   1.0000
   3.000   0.8636   0.00864   0.00287  -0.1106   0.5006   1.0000
   3.250   0.8916   0.00879   0.00299  -0.1107   0.4923   1.0000
   3.500   0.9194   0.00897   0.00313  -0.1108   0.4847   1.0000
   3.750   0.9474   0.00911   0.00325  -0.1109   0.4762   1.0000
   4.000   0.9750   0.00930   0.00339  -0.1109   0.4682   1.0000
   4.250   1.0029   0.00942   0.00352  -0.1110   0.4585   1.0000
   4.500   1.0304   0.00956   0.00366  -0.1110   0.4453   1.0000
   4.750   1.0578   0.00972   0.00379  -0.1110   0.4316   1.0000
   5.000   1.0851   0.00989   0.00393  -0.1110   0.4166   1.0000
   5.250   1.1123   0.01007   0.00409  -0.1110   0.4027   1.0000
   5.500   1.1389   0.01032   0.00428  -0.1109   0.3816   1.0000
   5.750   1.1644   0.01073   0.00450  -0.1107   0.3388   1.0000
   6.000   1.1869   0.01160   0.00494  -0.1103   0.2604   1.0000
   6.250   1.2040   0.01331   0.00592  -0.1093   0.1448   1.0000
   6.500   1.2253   0.01433   0.00662  -0.1086   0.0944   1.0000
   6.750   1.2422   0.01590   0.00772  -0.1073   0.0214   1.0000
   7.000   1.2657   0.01649   0.00836  -0.1067   0.0181   1.0000
   7.250   1.2893   0.01704   0.00903  -0.1060   0.0163   1.0000
   7.500   1.3119   0.01768   0.00979  -0.1052   0.0154   1.0000
   7.750   1.3336   0.01837   0.01060  -0.1043   0.0146   1.0000
   8.000   1.3539   0.01920   0.01152  -0.1032   0.0137   1.0000
   8.250   1.3726   0.02013   0.01255  -0.1019   0.0131   1.0000
   8.500   1.3893   0.02118   0.01371  -0.1003   0.0126   1.0000
   8.750   1.4034   0.02240   0.01501  -0.0983   0.0121   1.0000
   9.000   1.4142   0.02378   0.01649  -0.0959   0.0118   1.0000
   9.250   1.4211   0.02532   0.01813  -0.0929   0.0115   1.0000
   9.500   1.4242   0.02696   0.01987  -0.0894   0.0113   1.0000
   9.750   1.4253   0.02862   0.02160  -0.0856   0.0112   1.0000
  10.000   1.4260   0.03066   0.02371  -0.0821   0.0111   1.0000
  10.250   1.4296   0.03324   0.02633  -0.0792   0.0108   1.0000
  10.500   1.4376   0.03466   0.02790  -0.0771   0.0104   1.0000
  10.750   1.4469   0.03618   0.02953  -0.0752   0.0102   1.0000
  11.000   1.4566   0.03807   0.03153  -0.0733   0.0102   1.0000
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