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GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
Reynolds number: 100,000
Max Cl/Cd: 56.79 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe116-il-100000-n5.txt
Download as CSV file: xf-goe116-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 116 (MVA MK.3) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3783   0.09203   0.08756  -0.0378   1.0000   0.0214
  -8.500  -0.3782   0.08799   0.08360  -0.0397   1.0000   0.0209
  -8.250  -0.3802   0.08394   0.07965  -0.0414   1.0000   0.0204
  -8.000  -0.3857   0.08017   0.07600  -0.0427   1.0000   0.0200
  -7.750  -0.3962   0.07685   0.07284  -0.0432   1.0000   0.0197
  -7.500  -0.3869   0.06949   0.06551  -0.0524   0.9835   0.0190
  -7.250  -0.3711   0.05711   0.05303  -0.0690   0.9624   0.0180
  -7.000  -0.3489   0.04145   0.03655  -0.0879   0.9439   0.0169
  -6.750  -0.3225   0.03559   0.02995  -0.0934   0.9309   0.0165
  -6.500  -0.2949   0.03182   0.02556  -0.0961   0.9193   0.0164
  -6.250  -0.2666   0.02900   0.02223  -0.0977   0.9087   0.0164
  -6.000  -0.2384   0.02678   0.01961  -0.0986   0.8986   0.0167
  -5.750  -0.2118   0.02499   0.01752  -0.0991   0.8878   0.0180
  -5.500  -0.1844   0.02355   0.01573  -0.0995   0.8782   0.0196
  -5.250  -0.1563   0.02238   0.01425  -0.0997   0.8699   0.0205
  -5.000  -0.1288   0.02141   0.01297  -0.0998   0.8603   0.0213
  -4.750  -0.1005   0.02051   0.01172  -0.0999   0.8519   0.0224
  -4.500  -0.0721   0.01962   0.01049  -0.1001   0.8443   0.0246
  -4.250  -0.0441   0.01848   0.00910  -0.1002   0.8364   0.0306
  -4.000  -0.0161   0.01776   0.00873  -0.1005   0.8297   0.1226
  -3.750   0.0129   0.01842   0.00903  -0.1004   0.8218   0.1521
  -3.500   0.0414   0.01850   0.00877  -0.1004   0.8156   0.1622
  -3.250   0.0689   0.01881   0.00894  -0.1005   0.8082   0.1771
  -3.000   0.0959   0.01909   0.00913  -0.1005   0.8022   0.1941
  -2.750   0.1235   0.01888   0.00875  -0.1005   0.7956   0.1985
  -2.500   0.1513   0.01859   0.00827  -0.1006   0.7896   0.2002
  -2.250   0.1792   0.01835   0.00782  -0.1006   0.7841   0.2019
  -2.000   0.2069   0.01815   0.00747  -0.1007   0.7778   0.2035
  -1.750   0.2344   0.01789   0.00714  -0.1006   0.7728   0.2052
  -1.500   0.2617   0.01771   0.00694  -0.1007   0.7667   0.2077
  -1.250   0.2890   0.01756   0.00674  -0.1007   0.7613   0.2107
  -1.000   0.3165   0.01743   0.00656  -0.1007   0.7563   0.2136
  -0.750   0.3437   0.01734   0.00644  -0.1007   0.7503   0.2160
  -0.500   0.3711   0.01724   0.00629  -0.1006   0.7456   0.2183
  -0.250   0.3980   0.01714   0.00624  -0.1006   0.7402   0.2208
   0.000   0.4250   0.01708   0.00622  -0.1005   0.7347   0.2238
   0.250   0.4523   0.01702   0.00615  -0.1004   0.7303   0.2275
   0.500   0.4792   0.01705   0.00621  -0.1004   0.7246   0.2316
   0.750   0.5063   0.01702   0.00626  -0.1004   0.7194   0.2361
   1.000   0.5341   0.01701   0.00626  -0.1003   0.7155   0.2429
   1.250   0.5610   0.01707   0.00645  -0.1005   0.7095   0.2517
   1.500   0.5885   0.01707   0.00656  -0.1005   0.7046   0.2645
   1.750   0.6164   0.01702   0.00666  -0.1006   0.7008   0.2878
   2.000   0.6363   0.01587   0.00705  -0.0994   0.6950   0.7228
   2.250   0.6679   0.01567   0.00714  -0.0999   0.6902   1.0000
   2.500   0.6956   0.01585   0.00733  -0.0998   0.6863   1.0000
   2.750   0.7218   0.01616   0.00771  -0.0997   0.6802   1.0000
   3.000   0.7490   0.01638   0.00799  -0.0997   0.6756   1.0000
   3.250   0.7764   0.01660   0.00831  -0.0996   0.6715   1.0000
   3.500   0.8023   0.01694   0.00880  -0.0995   0.6653   1.0000
   3.750   0.8295   0.01713   0.00910  -0.0993   0.6602   1.0000
   4.000   0.8554   0.01738   0.00954  -0.0990   0.6529   1.0000
   4.250   0.8788   0.01655   0.00868  -0.0965   0.6186   1.0000
   4.500   0.9009   0.01619   0.00835  -0.0946   0.5790   1.0000
   4.750   0.9166   0.01614   0.00784  -0.0913   0.4620   1.0000
   5.000   0.9077   0.01943   0.00919  -0.0862   0.1656   1.0000
   5.250   0.9109   0.02194   0.01086  -0.0830   0.0330   1.0000
   5.500   0.9272   0.02307   0.01211  -0.0812   0.0261   1.0000
   5.750   0.9436   0.02414   0.01343  -0.0794   0.0240   1.0000
   6.000   0.9587   0.02527   0.01477  -0.0775   0.0225   1.0000
   6.250   0.9715   0.02652   0.01619  -0.0753   0.0203   1.0000
   6.500   0.9809   0.02798   0.01776  -0.0728   0.0184   1.0000
   6.750   0.9870   0.02967   0.01954  -0.0699   0.0175   1.0000
   7.000   0.9930   0.03154   0.02145  -0.0669   0.0170   1.0000
   7.250   1.0107   0.03367   0.02353  -0.0652   0.0166   1.0000
   7.500   1.0393   0.03560   0.02552  -0.0649   0.0163   1.0000
   7.750   1.0667   0.03741   0.02751  -0.0643   0.0157   1.0000
   8.000   1.0923   0.03928   0.02962  -0.0636   0.0146   1.0000
   8.250   1.1187   0.04167   0.03236  -0.0630   0.0140   1.0000
   8.500   1.1423   0.04452   0.03552  -0.0620   0.0139   1.0000
   8.750   1.1608   0.04752   0.03887  -0.0606   0.0140   1.0000
   9.000   1.1744   0.05067   0.04240  -0.0587   0.0142   1.0000
   9.250   1.1834   0.05393   0.04602  -0.0565   0.0143   1.0000
   9.500   1.1880   0.05728   0.04972  -0.0541   0.0146   1.0000
   9.750   1.1882   0.06068   0.05344  -0.0514   0.0148   1.0000
  10.000   1.1829   0.06393   0.05698  -0.0483   0.0150   1.0000
  10.250   1.1743   0.06726   0.06057  -0.0454   0.0152   1.0000
  10.500   1.1634   0.07078   0.06433  -0.0429   0.0154   1.0000
  10.750   1.1507   0.07454   0.06832  -0.0410   0.0156   1.0000
  11.000   1.1366   0.07862   0.07261  -0.0397   0.0158   1.0000
  11.250   1.1218   0.08306   0.07723  -0.0389   0.0160   1.0000
  11.500   1.1274   0.08637   0.08069  -0.0382   0.0174   1.0000
  11.750   1.1055   0.09056   0.08519  -0.0383   0.0178   1.0000
  12.000   1.0812   0.09605   0.09095  -0.0398   0.0182   1.0000
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