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GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)
Reynolds number: 100,000
Max Cl/Cd: 55.72 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe199-il-100000.txt
Download as CSV file: xf-goe199-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 199 (L.F.G. 5406) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3170   0.09111   0.08660  -0.0284   1.0000   0.0502
  -6.750  -0.3134   0.08792   0.08347  -0.0267   1.0000   0.0514
  -6.500  -0.3116   0.08548   0.08108  -0.0260   1.0000   0.0528
  -6.250  -0.3119   0.08343   0.07909  -0.0253   1.0000   0.0545
  -6.000  -0.3125   0.08158   0.07727  -0.0250   1.0000   0.0564
  -5.750  -0.3075   0.08014   0.07582  -0.0271   1.0000   0.0589
  -5.500  -0.2796   0.08096   0.07632  -0.0375   1.0000   0.0604
  -5.250  -0.2858   0.07554   0.07111  -0.0330   1.0000   0.0612
  -5.000  -0.2866   0.07217   0.06783  -0.0298   1.0000   0.0623
  -4.750  -0.2813   0.06951   0.06519  -0.0286   1.0000   0.0640
  -4.500  -0.2701   0.06701   0.06267  -0.0291   1.0000   0.0666
  -4.250  -0.2485   0.06480   0.06034  -0.0324   1.0000   0.0711
  -4.000  -0.2171   0.06198   0.05729  -0.0379   0.9995   0.0742
  -3.750  -0.1910   0.05770   0.05305  -0.0402   0.9948   0.0788
  -3.500  -0.1356   0.05434   0.04934  -0.0494   0.9888   0.0880
  -3.250  -0.1010   0.05063   0.04563  -0.0532   0.9838   0.0943
  -3.000  -0.0565   0.04752   0.04227  -0.0591   0.9772   0.1042
  -2.750  -0.0101   0.04467   0.03920  -0.0648   0.9716   0.1185
  -2.500   0.0275   0.04205   0.03648  -0.0686   0.9647   0.1350
  -2.250   0.0699   0.03961   0.03390  -0.0730   0.9584   0.1553
  -2.000   0.1114   0.03719   0.03134  -0.0772   0.9520   0.1819
  -1.750   0.1510   0.03507   0.02910  -0.0808   0.9444   0.2239
  -1.500   0.1933   0.03235   0.02646  -0.0848   0.9401   0.2900
  -1.000   0.2725   0.02713   0.02142  -0.0895   0.9251   0.4416
  -0.750   0.3181   0.02517   0.01932  -0.0924   0.9129   0.4695
  -0.500   0.4010   0.02504   0.01778  -0.1002   0.9005   0.2457
  -0.250   0.4521   0.02383   0.01573  -0.1007   0.8891   0.1405
   0.000   0.4898   0.02256   0.01416  -0.1006   0.8773   0.1254
   0.250   0.5221   0.02167   0.01297  -0.0997   0.8640   0.1134
   0.500   0.5499   0.02070   0.01192  -0.0984   0.8494   0.1076
   0.750   0.5771   0.02006   0.01111  -0.0969   0.8344   0.1029
   1.000   0.6034   0.01959   0.01054  -0.0953   0.8189   0.1009
   1.250   0.6289   0.01896   0.00988  -0.0937   0.8030   0.1006
   1.500   0.6534   0.01829   0.00922  -0.0920   0.7869   0.1033
   1.750   0.6786   0.01791   0.00882  -0.0907   0.7682   0.1093
   2.000   0.7042   0.01762   0.00844  -0.0894   0.7490   0.1138
   2.250   0.7302   0.01733   0.00807  -0.0882   0.7296   0.1219
   2.500   0.7565   0.01703   0.00776  -0.0869   0.7099   0.1504
   2.750   0.7832   0.01533   0.00752  -0.0861   0.6855   1.0000
   3.000   0.8085   0.01535   0.00727  -0.0848   0.6595   1.0000
   3.250   0.8334   0.01541   0.00711  -0.0836   0.6294   1.0000
   3.500   0.8580   0.01554   0.00700  -0.0824   0.5950   1.0000
   3.750   0.8820   0.01583   0.00697  -0.0812   0.5580   1.0000
   4.000   0.9057   0.01633   0.00718  -0.0801   0.5183   1.0000
   4.250   0.9293   0.01697   0.00749  -0.0791   0.4816   1.0000
   4.500   0.9533   0.01762   0.00790  -0.0784   0.4491   1.0000
   4.750   0.9778   0.01827   0.00833  -0.0778   0.4240   1.0000
   5.000   1.0028   0.01893   0.00886  -0.0774   0.4042   1.0000
   5.250   1.0281   0.01959   0.00941  -0.0770   0.3886   1.0000
   5.500   1.0537   0.02028   0.00997  -0.0767   0.3763   1.0000
   5.750   1.0795   0.02094   0.01063  -0.0765   0.3654   1.0000
   6.000   1.1055   0.02167   0.01139  -0.0763   0.3568   1.0000
   6.250   1.1319   0.02241   0.01211  -0.0762   0.3499   1.0000
   6.500   1.1582   0.02322   0.01298  -0.0761   0.3442   1.0000
   6.750   1.1842   0.02401   0.01390  -0.0760   0.3388   1.0000
   7.000   1.2109   0.02485   0.01480  -0.0760   0.3346   1.0000
   7.250   1.2365   0.02572   0.01579  -0.0758   0.3296   1.0000
   7.500   1.2605   0.02632   0.01653  -0.0754   0.3211   1.0000
   7.750   1.2833   0.02685   0.01719  -0.0748   0.3106   1.0000
   8.000   1.3071   0.02736   0.01766  -0.0743   0.3007   1.0000
   8.250   1.3289   0.02777   0.01828  -0.0735   0.2906   1.0000
   8.500   1.3492   0.02807   0.01873  -0.0725   0.2780   1.0000
   8.750   1.3684   0.02827   0.01909  -0.0713   0.2644   1.0000
   9.000   1.3850   0.02827   0.01924  -0.0697   0.2479   1.0000
   9.250   1.3968   0.02811   0.01924  -0.0673   0.2257   1.0000
   9.500   1.4031   0.02795   0.01936  -0.0640   0.1758   1.0000
   9.750   1.3993   0.03052   0.02107  -0.0604   0.0876   1.0000
  10.000   1.3977   0.03307   0.02362  -0.0567   0.0761   1.0000
  10.250   1.3903   0.03554   0.02614  -0.0525   0.0705   1.0000
  10.500   1.3892   0.03749   0.02832  -0.0490   0.0658   1.0000
  10.750   1.3847   0.03983   0.03079  -0.0459   0.0626   1.0000
  11.000   1.3778   0.04256   0.03360  -0.0431   0.0604   1.0000
  11.250   1.3740   0.04533   0.03640  -0.0407   0.0586   1.0000
  11.500   1.3780   0.04758   0.03881  -0.0388   0.0566   1.0000
  11.750   1.3826   0.04989   0.04124  -0.0371   0.0542   1.0000
  12.000   1.3881   0.05224   0.04362  -0.0356   0.0516   1.0000
  12.250   1.4230   0.05441   0.04549  -0.0341   0.0484   1.0000
  12.500   1.4385   0.05682   0.04815  -0.0328   0.0477   1.0000
  12.750   1.4506   0.05963   0.05123  -0.0315   0.0470   1.0000
  13.000   1.4546   0.06269   0.05458  -0.0300   0.0463   1.0000
  13.250   1.4529   0.06598   0.05816  -0.0286   0.0455   1.0000
  13.500   1.4476   0.06953   0.06200  -0.0274   0.0449   1.0000
  13.750   1.4391   0.07344   0.06618  -0.0266   0.0444   1.0000
  14.000   1.4273   0.07776   0.07079  -0.0261   0.0442   1.0000
  14.250   1.4123   0.08258   0.07589  -0.0263   0.0443   1.0000
  14.500   1.3946   0.08789   0.08148  -0.0271   0.0445   1.0000
  14.750   1.3749   0.09371   0.08756  -0.0287   0.0448   1.0000
  15.000   1.3535   0.10008   0.09419  -0.0312   0.0451   1.0000
  15.250   1.3309   0.10704   0.10138  -0.0345   0.0454   1.0000
  15.500   1.3075   0.11470   0.10926  -0.0388   0.0458   1.0000
  15.750   1.2835   0.12314   0.11789  -0.0439   0.0463   1.0000
  16.000   1.2593   0.13239   0.12731  -0.0500   0.0468   1.0000
  16.250   1.2363   0.14220   0.13726  -0.0564   0.0475   1.0000
  16.500   1.2168   0.15194   0.14708  -0.0624   0.0481   1.0000
  16.750   1.1321   0.18780   0.18300  -0.0870   0.0586   1.0000
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