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GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il)
Reynolds number: 500,000
Max Cl/Cd: 86.34 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe147-il-500000-n5.txt
Download as CSV file: xf-goe147-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 147 (MVA H.6) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4926   0.08813   0.08608   0.0063   1.0000   0.0062
  -8.000  -0.4919   0.08361   0.08159   0.0034   1.0000   0.0062
  -7.500  -0.5003   0.02917   0.02600  -0.0520   1.0000   0.0060
  -7.250  -0.4751   0.02230   0.01844  -0.0559   1.0000   0.0061
  -7.000  -0.4491   0.02014   0.01600  -0.0568   1.0000   0.0064
  -6.750  -0.4225   0.01899   0.01472  -0.0571   1.0000   0.0067
  -6.500  -0.3956   0.01796   0.01354  -0.0573   1.0000   0.0071
  -6.250  -0.3686   0.01683   0.01221  -0.0575   1.0000   0.0075
  -6.000  -0.3414   0.01563   0.01079  -0.0576   1.0000   0.0079
  -5.750  -0.3140   0.01454   0.00951  -0.0576   1.0000   0.0082
  -5.500  -0.2857   0.01368   0.00847  -0.0577   0.9976   0.0086
  -5.250  -0.2511   0.01260   0.00720  -0.0593   0.9785   0.0091
  -5.000  -0.2156   0.01185   0.00633  -0.0609   0.9491   0.0099
  -4.750  -0.1856   0.01146   0.00578  -0.0610   0.8995   0.0108
  -4.500  -0.1612   0.01126   0.00533  -0.0598   0.8485   0.0119
  -4.250  -0.1353   0.01105   0.00486  -0.0590   0.8047   0.0128
  -4.000  -0.1084   0.01063   0.00417  -0.0585   0.7646   0.0144
  -3.750  -0.0812   0.01042   0.00374  -0.0581   0.7229   0.0165
  -3.500  -0.0537   0.01031   0.00341  -0.0578   0.6815   0.0192
  -3.250  -0.0259   0.01010   0.00300  -0.0576   0.6477   0.0245
  -3.000   0.0022   0.00991   0.00266  -0.0575   0.6239   0.0325
  -2.750   0.0303   0.00966   0.00257  -0.0575   0.6055   0.0814
  -2.500   0.0587   0.00978   0.00258  -0.0573   0.5891   0.0898
  -2.250   0.0870   0.00994   0.00262  -0.0572   0.5733   0.0960
  -2.000   0.1153   0.00997   0.00255  -0.0571   0.5588   0.0997
  -1.750   0.1436   0.00996   0.00248  -0.0570   0.5434   0.1037
  -1.500   0.1719   0.00992   0.00235  -0.0569   0.5286   0.1050
  -1.250   0.2002   0.00992   0.00226  -0.0568   0.5126   0.1072
  -1.000   0.2285   0.00992   0.00217  -0.0568   0.4984   0.1089
  -0.750   0.2568   0.00987   0.00206  -0.0567   0.4843   0.1094
  -0.500   0.2852   0.00985   0.00196  -0.0566   0.4679   0.1099
  -0.250   0.3134   0.00985   0.00187  -0.0566   0.4497   0.1104
   0.000   0.3417   0.00986   0.00180  -0.0565   0.4286   0.1108
   0.250   0.3698   0.00993   0.00175  -0.0565   0.3998   0.1113
   0.500   0.3977   0.01004   0.00171  -0.0565   0.3641   0.1122
   0.750   0.4256   0.01015   0.00170  -0.0565   0.3372   0.1137
   1.250   0.4816   0.01035   0.00175  -0.0564   0.3024   0.1176
   1.500   0.5097   0.01043   0.00180  -0.0564   0.2898   0.1191
   1.750   0.5378   0.01051   0.00185  -0.0564   0.2786   0.1208
   2.000   0.5659   0.01061   0.00191  -0.0563   0.2689   0.1228
   2.250   0.5939   0.01070   0.00198  -0.0563   0.2595   0.1249
   2.500   0.6220   0.01078   0.00207  -0.0563   0.2522   0.1288
   2.750   0.6499   0.01087   0.00217  -0.0563   0.2445   0.1362
   3.000   0.6780   0.01090   0.00231  -0.0563   0.2379   0.1709
   3.250   0.7059   0.01099   0.00246  -0.0563   0.2307   0.1997
   3.500   0.7338   0.01108   0.00259  -0.0562   0.2244   0.2218
   3.750   0.7616   0.01117   0.00274  -0.0562   0.2173   0.2451
   4.000   0.7898   0.01084   0.00297  -0.0567   0.2107   0.5026
   4.250   0.8106   0.00991   0.00310  -0.0550   0.2041   1.0000
   4.500   0.8382   0.01011   0.00327  -0.0549   0.1968   1.0000
   4.750   0.8658   0.01031   0.00346  -0.0548   0.1883   1.0000
   5.000   0.8932   0.01053   0.00365  -0.0547   0.1798   1.0000
   5.250   0.9205   0.01078   0.00387  -0.0547   0.1700   1.0000
   5.500   0.9477   0.01102   0.00410  -0.0546   0.1603   1.0000
   5.750   0.9748   0.01129   0.00436  -0.0545   0.1523   1.0000
   6.250   1.0282   0.01192   0.00494  -0.0542   0.1354   1.0000
   6.500   1.0547   0.01226   0.00526  -0.0541   0.1280   1.0000
   6.750   1.0811   0.01259   0.00561  -0.0539   0.1212   1.0000
   7.000   1.1073   0.01296   0.00597  -0.0537   0.1131   1.0000
   7.250   1.1332   0.01336   0.00635  -0.0535   0.1039   1.0000
   7.500   1.1592   0.01372   0.00671  -0.0533   0.0921   1.0000
   7.750   1.1782   0.01542   0.00799  -0.0527   0.0235   1.0000
   8.000   1.2025   0.01609   0.00869  -0.0523   0.0150   1.0000
   8.250   1.2265   0.01676   0.00942  -0.0518   0.0116   1.0000
   8.500   1.2508   0.01735   0.01010  -0.0514   0.0101   1.0000
   8.750   1.2745   0.01799   0.01082  -0.0510   0.0088   1.0000
   9.000   1.2970   0.01881   0.01172  -0.0504   0.0079   1.0000
   9.250   1.3189   0.01969   0.01272  -0.0498   0.0072   1.0000
   9.500   1.3409   0.02050   0.01363  -0.0492   0.0068   1.0000
   9.750   1.3621   0.02134   0.01460  -0.0485   0.0062   1.0000
  10.000   1.3827   0.02222   0.01556  -0.0478   0.0058   1.0000
  10.250   1.4012   0.02330   0.01673  -0.0470   0.0053   1.0000
  10.500   1.4176   0.02458   0.01815  -0.0459   0.0050   1.0000
  10.750   1.4340   0.02575   0.01944  -0.0449   0.0048   1.0000
  11.000   1.4483   0.02704   0.02088  -0.0437   0.0046   1.0000
  11.250   1.4604   0.02845   0.02242  -0.0423   0.0044   1.0000
  11.500   1.4697   0.02998   0.02408  -0.0407   0.0042   1.0000
  11.750   1.4744   0.03161   0.02584  -0.0387   0.0041   1.0000
  12.000   1.4737   0.03351   0.02787  -0.0366   0.0040   1.0000
  12.250   1.4719   0.03594   0.03044  -0.0356   0.0039   1.0000
  12.500   1.4682   0.03914   0.03381  -0.0359   0.0038   1.0000
  12.750   1.4634   0.04313   0.03795  -0.0374   0.0038   1.0000
  13.000   1.4563   0.04792   0.04290  -0.0398   0.0037   1.0000
  13.250   1.4472   0.05328   0.04840  -0.0425   0.0037   1.0000
  13.500   1.4348   0.05916   0.05443  -0.0453   0.0036   1.0000
  13.750   1.4203   0.06533   0.06074  -0.0480   0.0036   1.0000
  14.000   1.4044   0.07176   0.06731  -0.0508   0.0036   1.0000
  14.250   1.3880   0.07829   0.07396  -0.0535   0.0036   1.0000
  14.500   1.3718   0.08483   0.08062  -0.0561   0.0036   1.0000
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