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GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il)
Reynolds number: 500,000
Max Cl/Cd: 74.78 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe114-il-500000-n5.txt
Download as CSV file: xf-goe114-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3626   0.09160   0.08945  -0.0433   1.0000   0.0039
  -8.750  -0.3629   0.08805   0.08594  -0.0441   1.0000   0.0039
  -8.500  -0.3649   0.08466   0.08259  -0.0445   1.0000   0.0039
  -8.250  -0.3554   0.07930   0.07725  -0.0491   0.9933   0.0039
  -8.000  -0.3447   0.07383   0.07178  -0.0545   0.9849   0.0039
  -7.750  -0.3322   0.06723   0.06519  -0.0615   0.9753   0.0039
  -7.500  -0.3161   0.05851   0.05640  -0.0746   0.9627   0.0039
  -7.250  -0.2911   0.04898   0.04662  -0.0932   0.9466   0.0039
  -7.000  -0.2750   0.04347   0.04078  -0.1006   0.9302   0.0039
  -6.750  -0.2619   0.03950   0.03648  -0.1034   0.9145   0.0039
  -6.500  -0.2484   0.03613   0.03278  -0.1044   0.9008   0.0039
  -6.000  -0.2171   0.03010   0.02603  -0.1043   0.8770   0.0039
  -5.750  -0.1995   0.02707   0.02265  -0.1038   0.8668   0.0040
  -5.250  -0.1625   0.02084   0.01581  -0.1029   0.8485   0.0031
  -5.000  -0.1392   0.01871   0.01333  -0.1019   0.8399   0.0029
  -4.750  -0.1146   0.01696   0.01127  -0.1010   0.8323   0.0029
  -4.500  -0.0890   0.01574   0.00977  -0.1002   0.8246   0.0044
  -4.250  -0.0639   0.01482   0.00872  -0.0998   0.8179   0.0054
  -4.000  -0.0386   0.01335   0.00708  -0.0989   0.8108   0.0047
  -3.750  -0.0137   0.01224   0.00583  -0.0980   0.8043   0.0044
  -3.500   0.0111   0.01136   0.00485  -0.0974   0.7972   0.0043
  -3.250   0.0362   0.01063   0.00398  -0.0969   0.7909   0.0045
  -3.000   0.0620   0.01003   0.00326  -0.0965   0.7840   0.0050
  -2.750   0.0886   0.00969   0.00277  -0.0963   0.7779   0.0066
  -2.500   0.1152   0.00923   0.00214  -0.0960   0.7712   0.0091
  -2.250   0.1423   0.00903   0.00176  -0.0958   0.7650   0.0156
  -2.000   0.1653   0.00788   0.00140  -0.0956   0.7584   0.2668
  -1.750   0.1925   0.00787   0.00138  -0.0956   0.7518   0.3033
  -1.500   0.2198   0.00788   0.00138  -0.0955   0.7453   0.3196
  -1.250   0.2471   0.00788   0.00132  -0.0955   0.7385   0.3238
  -1.000   0.2743   0.00787   0.00125  -0.0955   0.7317   0.3273
  -0.750   0.3013   0.00789   0.00120  -0.0954   0.7227   0.3306
  -0.500   0.3281   0.00789   0.00117  -0.0952   0.7121   0.3337
  -0.250   0.3549   0.00790   0.00116  -0.0951   0.7026   0.3370
   0.000   0.3818   0.00792   0.00116  -0.0950   0.6939   0.3416
   0.250   0.4089   0.00794   0.00118  -0.0950   0.6852   0.3457
   0.500   0.4356   0.00795   0.00121  -0.0949   0.6766   0.3492
   0.750   0.4624   0.00798   0.00126  -0.0948   0.6671   0.3528
   1.000   0.4879   0.00806   0.00130  -0.0943   0.6442   0.3575
   1.250   0.5106   0.00828   0.00135  -0.0934   0.5972   0.3611
   1.500   0.5274   0.00892   0.00152  -0.0913   0.4937   0.3646
   1.750   0.5270   0.01137   0.00242  -0.0869   0.1294   0.3674
   2.000   0.5477   0.01206   0.00285  -0.0857   0.0127   0.3712
   2.250   0.5728   0.01228   0.00321  -0.0852   0.0091   0.3751
   2.500   0.5965   0.01264   0.00372  -0.0844   0.0060   0.3791
   2.750   0.6194   0.01309   0.00430  -0.0835   0.0050   0.3835
   3.250   0.6606   0.01437   0.00578  -0.0807   0.0048   0.3924
   3.500   0.6787   0.01520   0.00671  -0.0788   0.0047   0.3974
   3.750   0.6985   0.01587   0.00747  -0.0773   0.0030   0.4031
   4.000   0.7163   0.01682   0.00854  -0.0753   0.0028   0.4093
   4.250   0.7356   0.01794   0.00975  -0.0736   0.0027   0.4172
   4.500   0.7586   0.01936   0.01126  -0.0723   0.0027   0.4275
   4.750   0.7872   0.02117   0.01320  -0.0717   0.0032   0.4430
   5.250   0.8218   0.01099   0.00440  -0.0679   0.0046   0.7191
   5.750   0.9030   0.03092   0.02468  -0.0719   0.0041   1.0000
   6.250   0.9415   0.03544   0.02970  -0.0682   0.0041   1.0000
   6.500   0.9586   0.03773   0.03224  -0.0661   0.0041   1.0000
   6.750   0.9743   0.03995   0.03473  -0.0637   0.0040   1.0000
   7.000   0.9893   0.04207   0.03712  -0.0612   0.0040   1.0000
   7.250   1.0072   0.04354   0.03889  -0.0583   0.0037   1.0000
   7.500   1.0209   0.04608   0.04170  -0.0556   0.0035   1.0000
   7.750   1.0305   0.04897   0.04482  -0.0529   0.0034   1.0000
   8.000   1.0374   0.05205   0.04813  -0.0501   0.0032   1.0000
   8.250   1.0416   0.05517   0.05149  -0.0472   0.0031   1.0000
   8.500   1.0425   0.05834   0.05487  -0.0442   0.0031   1.0000
   8.750   1.0400   0.06156   0.05827  -0.0412   0.0030   1.0000
   9.000   1.0343   0.06468   0.06157  -0.0381   0.0030   1.0000
   9.250   1.0225   0.06747   0.06450  -0.0343   0.0029   1.0000
   9.500   1.0079   0.07021   0.06737  -0.0309   0.0030   1.0000
   9.750   0.9915   0.07328   0.07056  -0.0284   0.0030   1.0000
  10.000   0.9740   0.07675   0.07415  -0.0269   0.0030   1.0000
  10.250   0.9555   0.08076   0.07828  -0.0265   0.0030   1.0000
  10.500   0.9370   0.08529   0.08291  -0.0272   0.0030   1.0000
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