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GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il)
Reynolds number: 50,000
Max Cl/Cd: 39.62 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe122-il-50000-n5.txt
Download as CSV file: xf-goe122-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 122 (MVA H.2) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4129   0.11646   0.10968  -0.0059   1.0000   0.0788
  -8.750  -0.4159   0.11532   0.10865  -0.0100   1.0000   0.0804
  -8.500  -0.4191   0.11404   0.10748  -0.0145   1.0000   0.0810
  -8.250  -0.3954   0.10614   0.09954  -0.0095   1.0000   0.0862
  -8.000  -0.3899   0.10314   0.09660  -0.0108   1.0000   0.0903
  -7.750  -0.3903   0.10111   0.09466  -0.0141   1.0000   0.0940
  -7.500  -0.3884   0.09970   0.09334  -0.0230   1.0000   0.0956
  -7.250  -0.3774   0.09409   0.08779  -0.0194   1.0000   0.0979
  -7.000  -0.3670   0.09037   0.08408  -0.0188   1.0000   0.1019
  -6.750  -0.3586   0.08738   0.08113  -0.0224   1.0000   0.1074
  -6.500  -0.3486   0.08467   0.07845  -0.0310   1.0000   0.1112
  -6.000  -0.3252   0.07853   0.07230  -0.0365   1.0000   0.1256
  -5.750  -0.3198   0.07406   0.06799  -0.0301   1.0000   0.1313
  -5.500  -0.3085   0.07118   0.06511  -0.0342   1.0000   0.1422
  -5.250  -0.3001   0.06815   0.06215  -0.0323   1.0000   0.1493
  -4.500  -0.2687   0.05991   0.05385  -0.0352   1.0000   0.1878
  -4.250  -0.2601   0.05736   0.05134  -0.0340   1.0000   0.2043
  -4.000  -0.1937   0.04865   0.04140  -0.0474   1.0000   0.0817
  -3.750  -0.1796   0.04576   0.03852  -0.0466   1.0000   0.0778
  -3.500  -0.1589   0.04266   0.03519  -0.0473   1.0000   0.0735
  -3.250  -0.1159   0.03870   0.03062  -0.0518   0.9933   0.0701
  -3.000  -0.0688   0.03567   0.02714  -0.0567   0.9818   0.0731
  -2.750  -0.0205   0.03259   0.02338  -0.0611   0.9705   0.0714
  -2.500   0.0255   0.03015   0.02037  -0.0647   0.9591   0.0711
  -2.250   0.0704   0.02839   0.01818  -0.0681   0.9485   0.0756
  -2.000   0.1141   0.02674   0.01608  -0.0708   0.9375   0.0768
  -1.750   0.1546   0.02540   0.01437  -0.0728   0.9250   0.0775
  -1.500   0.1928   0.02431   0.01298  -0.0743   0.9119   0.0786
  -1.250   0.2302   0.02347   0.01184  -0.0753   0.8982   0.0806
  -1.000   0.2652   0.02263   0.01094  -0.0763   0.8835   0.0867
  -0.750   0.2979   0.02206   0.01021  -0.0766   0.8678   0.0920
  -0.500   0.3289   0.02158   0.00955  -0.0765   0.8515   0.0957
  -0.250   0.3585   0.02108   0.00901  -0.0763   0.8350   0.1019
   0.000   0.3860   0.02074   0.00861  -0.0757   0.8165   0.1119
   0.250   0.4134   0.02021   0.00827  -0.0752   0.7983   0.1452
   0.750   0.4681   0.01808   0.00776  -0.0736   0.7630   1.0000
   1.000   0.4944   0.01820   0.00761  -0.0727   0.7450   1.0000
   1.250   0.5201   0.01838   0.00758  -0.0718   0.7260   1.0000
   1.500   0.5459   0.01856   0.00756  -0.0709   0.7077   1.0000
   1.750   0.5717   0.01876   0.00758  -0.0700   0.6901   1.0000
   2.000   0.5976   0.01898   0.00765  -0.0692   0.6734   1.0000
   2.250   0.6234   0.01924   0.00776  -0.0685   0.6572   1.0000
   2.500   0.6492   0.01954   0.00793  -0.0678   0.6412   1.0000
   2.750   0.6752   0.01988   0.00820  -0.0672   0.6258   1.0000
   3.000   0.7014   0.02024   0.00848  -0.0667   0.6113   1.0000
   3.250   0.7275   0.02063   0.00884  -0.0663   0.5970   1.0000
   3.500   0.7533   0.02104   0.00926  -0.0658   0.5829   1.0000
   3.750   0.7789   0.02145   0.00966  -0.0653   0.5685   1.0000
   4.000   0.8041   0.02184   0.01004  -0.0647   0.5536   1.0000
   4.250   0.8291   0.02220   0.01044  -0.0640   0.5382   1.0000
   4.500   0.8538   0.02254   0.01077  -0.0633   0.5223   1.0000
   4.750   0.8781   0.02292   0.01118  -0.0625   0.5060   1.0000
   5.000   0.9027   0.02333   0.01163  -0.0618   0.4913   1.0000
   5.250   0.9276   0.02379   0.01221  -0.0612   0.4786   1.0000
   5.500   0.9522   0.02433   0.01287  -0.0607   0.4660   1.0000
   5.750   0.9767   0.02488   0.01356  -0.0602   0.4533   1.0000
   6.000   1.0011   0.02546   0.01431  -0.0596   0.4408   1.0000
   6.250   1.0252   0.02605   0.01504  -0.0589   0.4280   1.0000
   6.500   1.0481   0.02659   0.01572  -0.0581   0.4118   1.0000
   6.750   1.0701   0.02709   0.01634  -0.0570   0.3933   1.0000
   7.000   1.0916   0.02755   0.01694  -0.0559   0.3744   1.0000
   7.250   1.1114   0.02809   0.01770  -0.0548   0.3531   1.0000
   7.500   1.1300   0.02852   0.01826  -0.0535   0.3291   1.0000
   7.750   1.1494   0.02917   0.01918  -0.0524   0.3084   1.0000
   8.000   1.1674   0.02978   0.01999  -0.0511   0.2847   1.0000
   8.250   1.1837   0.03054   0.02101  -0.0498   0.2542   1.0000
   8.500   1.1951   0.03164   0.02203  -0.0481   0.2076   1.0000
   8.750   1.1995   0.03365   0.02365  -0.0461   0.1602   1.0000
   9.000   1.2045   0.03596   0.02587  -0.0443   0.1128   1.0000
   9.250   1.2051   0.03856   0.02826  -0.0424   0.0914   1.0000
   9.500   1.2025   0.04125   0.03085  -0.0404   0.0814   1.0000
   9.750   1.1989   0.04398   0.03362  -0.0385   0.0747   1.0000
  10.000   1.1939   0.04705   0.03675  -0.0372   0.0700   1.0000
  10.250   1.1887   0.05034   0.04009  -0.0363   0.0670   1.0000
  10.500   1.1872   0.05344   0.04340  -0.0356   0.0633   1.0000
  10.750   1.1843   0.05679   0.04692  -0.0352   0.0598   1.0000
  11.000   1.1805   0.06030   0.05047  -0.0349   0.0569   1.0000
  11.250   1.1820   0.06332   0.05362  -0.0339   0.0544   1.0000
  11.500   1.1859   0.06620   0.05677  -0.0330   0.0519   1.0000
  11.750   1.1884   0.06931   0.06006  -0.0324   0.0490   1.0000
  12.000   1.1916   0.07232   0.06315  -0.0315   0.0463   1.0000
  12.250   1.2052   0.07466   0.06556  -0.0290   0.0439   1.0000
  12.500   1.2041   0.07869   0.06994  -0.0292   0.0430   1.0000
  12.750   1.1984   0.08333   0.07490  -0.0301   0.0421   1.0000
  13.000   1.1895   0.08850   0.08037  -0.0317   0.0414   1.0000
  13.250   1.1781   0.09419   0.08633  -0.0339   0.0409   1.0000
  13.500   1.1645   0.10045   0.09285  -0.0367   0.0406   1.0000
  13.750   1.1491   0.10734   0.09996  -0.0402   0.0406   1.0000
  14.000   1.1324   0.11488   0.10771  -0.0444   0.0407   1.0000
  14.250   1.1146   0.12317   0.11619  -0.0492   0.0411   1.0000
  14.500   1.0965   0.13223   0.12540  -0.0546   0.0416   1.0000
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