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GOE 459 AIRFOIL (goe459-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 459 AIRFOIL (goe459-il)
Reynolds number: 50,000
Max Cl/Cd: 28.6 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe459-il-50000.txt
Download as CSV file: xf-goe459-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 459 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6495   0.09094   0.08311  -0.0246   1.0000   0.2097
 -10.250  -0.6543   0.08497   0.07715  -0.0262   1.0000   0.2063
 -10.000  -0.8429   0.06711   0.05930  -0.0290   1.0000   0.1800
  -9.750  -0.8615   0.06286   0.05487  -0.0259   1.0000   0.1796
  -9.500  -0.8797   0.05886   0.05060  -0.0223   1.0000   0.1796
  -9.250  -0.8962   0.05520   0.04658  -0.0183   1.0000   0.1802
  -9.000  -0.8707   0.05300   0.04456  -0.0178   1.0000   0.1864
  -8.750  -0.8746   0.04985   0.04112  -0.0145   1.0000   0.1883
  -8.500  -0.8761   0.04678   0.03768  -0.0112   1.0000   0.1901
  -8.250  -0.8756   0.04397   0.03445  -0.0078   1.0000   0.1928
  -8.000  -0.8700   0.04150   0.03165  -0.0048   1.0000   0.1972
  -7.750  -0.8524   0.03964   0.02977  -0.0032   1.0000   0.2034
  -7.500  -0.8426   0.03746   0.02720  -0.0005   1.0000   0.2087
  -7.250  -0.8248   0.03544   0.02506   0.0011   1.0000   0.2147
  -7.000  -0.8087   0.03376   0.02316   0.0031   1.0000   0.2237
  -6.750  -0.7897   0.03224   0.02167   0.0047   1.0000   0.2356
  -6.500  -0.7714   0.03071   0.02012   0.0065   1.0000   0.2506
  -6.250  -0.7535   0.02915   0.01851   0.0084   1.0000   0.2708
  -6.000  -0.7355   0.02761   0.01716   0.0104   1.0000   0.3012
  -5.750  -0.7208   0.02621   0.01613   0.0131   1.0000   0.3432
  -5.500  -0.7081   0.02517   0.01544   0.0163   1.0000   0.3888
  -5.250  -0.6960   0.02446   0.01500   0.0197   1.0000   0.4342
  -5.000  -0.6840   0.02391   0.01468   0.0232   1.0000   0.4804
  -4.750  -0.6716   0.02356   0.01455   0.0270   1.0000   0.5285
  -4.500  -0.6582   0.02355   0.01484   0.0312   1.0000   0.5790
  -4.250  -0.6424   0.02381   0.01533   0.0355   1.0000   0.6297
  -4.000  -0.6224   0.02415   0.01578   0.0392   1.0000   0.6775
  -3.750  -0.5981   0.02452   0.01618   0.0421   1.0000   0.7216
  -3.500  -0.5619   0.02525   0.01685   0.0433   1.0000   0.7619
  -3.250  -0.5240   0.02595   0.01740   0.0437   1.0000   0.7992
  -3.000  -0.4510   0.02736   0.01856   0.0386   1.0000   0.8331
  -2.750  -0.3467   0.02883   0.01966   0.0277   1.0000   0.8657
  -2.500  -0.2662   0.02930   0.01986   0.0192   1.0000   0.8961
  -2.250  -0.1873   0.02914   0.01949   0.0098   1.0000   0.9211
  -2.000  -0.1261   0.02866   0.01887   0.0027   1.0000   0.9451
  -1.750  -0.0627   0.02797   0.01807  -0.0053   1.0000   0.9683
  -1.500   0.0087   0.02692   0.01692  -0.0153   1.0000   0.9906
  -1.250   0.0424   0.02618   0.01615  -0.0189   1.0000   1.0000
  -1.000   0.0399   0.02590   0.01592  -0.0159   1.0000   1.0000
  -0.750   0.0337   0.02572   0.01578  -0.0124   1.0000   1.0000
  -0.500   0.0243   0.02562   0.01571  -0.0085   1.0000   1.0000
  -0.250   0.0127   0.02558   0.01568  -0.0043   1.0000   1.0000
   0.000   0.0000   0.02557   0.01567   0.0000   1.0000   1.0000
   0.250  -0.0127   0.02558   0.01567   0.0043   1.0000   1.0000
   0.500  -0.0243   0.02562   0.01570   0.0085   1.0000   1.0000
   0.750  -0.0337   0.02572   0.01577   0.0124   1.0000   1.0000
   1.000  -0.0399   0.02590   0.01592   0.0159   1.0000   1.0000
   1.250  -0.0424   0.02617   0.01615   0.0189   1.0000   1.0000
   1.500  -0.0087   0.02692   0.01691   0.0153   0.9905   1.0000
   1.750   0.0628   0.02797   0.01806   0.0053   0.9683   1.0000
   2.000   0.1260   0.02865   0.01886  -0.0027   0.9452   1.0000
   2.250   0.1873   0.02913   0.01948  -0.0098   0.9211   1.0000
   2.500   0.2664   0.02929   0.01985  -0.0192   0.8961   1.0000
   2.750   0.3461   0.02883   0.01966  -0.0276   0.8658   1.0000
   3.000   0.4517   0.02733   0.01853  -0.0387   0.8330   1.0000
   3.250   0.5238   0.02595   0.01740  -0.0437   0.7993   1.0000
   3.500   0.5618   0.02524   0.01684  -0.0433   0.7619   1.0000
   3.750   0.5981   0.02451   0.01617  -0.0421   0.7216   1.0000
   4.000   0.6223   0.02415   0.01579  -0.0392   0.6777   1.0000
   4.250   0.6423   0.02380   0.01532  -0.0355   0.6297   1.0000
   4.500   0.6581   0.02355   0.01484  -0.0312   0.5791   1.0000
   4.750   0.6715   0.02355   0.01455  -0.0270   0.5285   1.0000
   5.000   0.6839   0.02391   0.01468  -0.0232   0.4805   1.0000
   5.250   0.6960   0.02446   0.01500  -0.0197   0.4344   1.0000
   5.500   0.7081   0.02517   0.01544  -0.0163   0.3890   1.0000
   5.750   0.7206   0.02620   0.01612  -0.0130   0.3429   1.0000
   6.000   0.7356   0.02760   0.01715  -0.0104   0.3014   1.0000
   6.250   0.7536   0.02915   0.01850  -0.0084   0.2709   1.0000
   6.500   0.7713   0.03072   0.02012  -0.0065   0.2505   1.0000
   6.750   0.7899   0.03225   0.02167  -0.0047   0.2359   1.0000
   7.000   0.8087   0.03376   0.02316  -0.0031   0.2237   1.0000
   7.250   0.8248   0.03544   0.02507  -0.0011   0.2149   1.0000
   7.500   0.8426   0.03746   0.02720   0.0005   0.2087   1.0000
   7.750   0.8524   0.03965   0.02978   0.0032   0.2035   1.0000
   8.000   0.8697   0.04151   0.03168   0.0048   0.1974   1.0000
   8.250   0.8759   0.04397   0.03445   0.0077   0.1929   1.0000
   8.500   0.8761   0.04678   0.03768   0.0112   0.1901   1.0000
   8.750   0.8747   0.04985   0.04111   0.0145   0.1883   1.0000
   9.000   0.8708   0.05301   0.04456   0.0178   0.1864   1.0000
   9.250   0.8962   0.05517   0.04655   0.0182   0.1801   1.0000
   9.500   0.8793   0.05886   0.05061   0.0224   0.1795   1.0000
   9.750   0.8610   0.06287   0.05488   0.0260   0.1795   1.0000
  10.000   0.8420   0.06713   0.05932   0.0290   0.1799   1.0000
  10.250   0.8218   0.07162   0.06392   0.0315   0.1804   1.0000
  10.500   0.4938   0.11489   0.10661  -0.0012   0.3744   1.0000
  10.750   0.5229   0.11987   0.11169  -0.0013   0.3680   1.0000
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