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GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il)
Reynolds number: 200,000
Max Cl/Cd: 50.81 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe114-il-200000-n5.txt
Download as CSV file: xf-goe114-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 114 (MVA MK.1) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3634   0.08750   0.08424  -0.0472   1.0000   0.0125
  -8.250  -0.3673   0.08382   0.08064  -0.0479   1.0000   0.0125
  -8.000  -0.3745   0.08059   0.07749  -0.0478   1.0000   0.0125
  -7.750  -0.3791   0.07683   0.07377  -0.0494   0.9978   0.0125
  -7.500  -0.3659   0.06943   0.06633  -0.0608   0.9864   0.0125
  -7.250  -0.3459   0.06141   0.05812  -0.0755   0.9750   0.0125
  -7.000  -0.3281   0.05527   0.05167  -0.0849   0.9661   0.0125
  -6.750  -0.3094   0.05030   0.04634  -0.0909   0.9576   0.0125
  -6.500  -0.2992   0.04255   0.03832  -0.0954   0.9481   0.0132
  -6.250  -0.2778   0.03741   0.03295  -0.0987   0.9426   0.0139
  -6.000  -0.2588   0.03372   0.02902  -0.1002   0.9338   0.0154
  -5.750  -0.2333   0.03074   0.02560  -0.1019   0.9276   0.0181
  -5.500  -0.2121   0.02773   0.02205  -0.1025   0.9192   0.0242
  -5.250  -0.1887   0.02521   0.01909  -0.1032   0.9123   0.0334
  -4.750  -0.1249   0.02148   0.01459  -0.1014   0.9001   0.0109
  -4.500  -0.0990   0.01954   0.01238  -0.1008   0.8925   0.0099
  -4.250  -0.0709   0.01798   0.01059  -0.1005   0.8863   0.0093
  -4.000  -0.0449   0.01671   0.00916  -0.0998   0.8786   0.0090
  -3.750  -0.0186   0.01557   0.00792  -0.0992   0.8719   0.0090
  -3.500   0.0065   0.01465   0.00691  -0.0987   0.8642   0.0094
  -3.250   0.0328   0.01403   0.00617  -0.0984   0.8573   0.0118
  -3.000   0.0591   0.01334   0.00526  -0.0980   0.8502   0.0128
  -2.750   0.0857   0.01265   0.00420  -0.0976   0.8433   0.0156
  -2.500   0.1130   0.01229   0.00360  -0.0974   0.8364   0.0222
  -2.250   0.1364   0.01109   0.00334  -0.0972   0.8295   0.3022
  -2.000   0.1638   0.01133   0.00348  -0.0970   0.8226   0.3454
  -1.750   0.1908   0.01135   0.00338  -0.0969   0.8155   0.3565
  -1.500   0.2181   0.01130   0.00322  -0.0968   0.8087   0.3614
  -1.250   0.2450   0.01126   0.00311  -0.0967   0.8017   0.3661
  -1.000   0.2722   0.01123   0.00298  -0.0966   0.7947   0.3715
  -0.750   0.2991   0.01119   0.00291  -0.0965   0.7877   0.3764
  -0.500   0.3261   0.01115   0.00285  -0.0964   0.7805   0.3812
  -0.250   0.3529   0.01113   0.00281  -0.0962   0.7732   0.3861
   0.000   0.3798   0.01109   0.00277  -0.0961   0.7661   0.3902
   0.250   0.4064   0.01105   0.00278  -0.0960   0.7583   0.3942
   0.500   0.4333   0.01104   0.00277  -0.0958   0.7511   0.3991
   0.750   0.4597   0.01101   0.00284  -0.0956   0.7428   0.4039
   1.000   0.4865   0.01099   0.00287  -0.0955   0.7356   0.4088
   1.250   0.5127   0.01098   0.00296  -0.0952   0.7260   0.4142
   1.500   0.5369   0.01092   0.00296  -0.0943   0.7010   0.4195
   1.750   0.5569   0.01096   0.00279  -0.0923   0.6367   0.4255
   2.000   0.5701   0.01157   0.00279  -0.0891   0.5103   0.4315
   2.750   0.6033   0.01562   0.00512  -0.0807   0.0133   0.4570
   3.250   0.6460   0.01644   0.00658  -0.0782   0.0099   0.5108
   3.500   0.6605   0.01640   0.00749  -0.0755   0.0095   0.7863
   4.000   0.7080   0.01864   0.01005  -0.0743   0.0095   1.0000
   4.250   0.7258   0.01985   0.01131  -0.0723   0.0098   1.0000
   4.500   0.7471   0.02138   0.01285  -0.0707   0.0106   1.0000
   4.750   0.7725   0.02287   0.01439  -0.0698   0.0099   1.0000
   5.000   0.7992   0.02475   0.01625  -0.0696   0.0081   1.0000
   5.250   0.8318   0.02668   0.01838  -0.0691   0.0108   1.0000
   6.750   0.9266   0.03181   0.02533  -0.0568   0.0132   1.0000
   7.000   0.9389   0.03324   0.02713  -0.0539   0.0127   1.0000
   7.250   0.9521   0.03458   0.02884  -0.0508   0.0117   1.0000
   7.500   0.9610   0.03755   0.03211  -0.0481   0.0110   1.0000
   7.750   0.9667   0.04089   0.03571  -0.0453   0.0105   1.0000
   8.000   0.9689   0.04441   0.03949  -0.0424   0.0102   1.0000
   8.250   0.9677   0.04801   0.04332  -0.0394   0.0099   1.0000
   8.500   0.9625   0.05159   0.04711  -0.0363   0.0097   1.0000
   8.750   0.9522   0.05491   0.05066  -0.0327   0.0095   1.0000
   9.000   0.9370   0.05801   0.05393  -0.0290   0.0095   1.0000
   9.250   0.9195   0.06131   0.05738  -0.0260   0.0094   1.0000
   9.500   0.9002   0.06499   0.06122  -0.0238   0.0095   1.0000
   9.750   0.8791   0.06912   0.06550  -0.0225   0.0095   1.0000
  10.000   0.8569   0.07373   0.07027  -0.0220   0.0096   1.0000
  10.250   0.8338   0.07884   0.07546  -0.0225   0.0097   1.0000
  10.500   0.8102   0.08442   0.08117  -0.0239   0.0099   1.0000
  10.750   0.7865   0.09042   0.08729  -0.0262   0.0102   1.0000
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