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GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 426 AIRFOIL (goe426-il)
Reynolds number: 100,000
Max Cl/Cd: 52.14 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe426-il-100000-n5.txt
Download as CSV file: xf-goe426-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 426 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2623   0.10653   0.10162  -0.0459   1.0000   0.0792
  -9.500  -0.2880   0.10502   0.10028  -0.0480   1.0000   0.0812
  -9.250  -0.2924   0.10065   0.09596  -0.0564   0.9865   0.0817
  -9.000  -0.2627   0.09603   0.09132  -0.0549   0.9827   0.0828
  -8.750  -0.2389   0.09248   0.08774  -0.0565   0.9744   0.0843
  -8.500  -0.2192   0.08869   0.08394  -0.0603   0.9646   0.0859
  -8.250  -0.2428   0.07284   0.06796  -0.0838   0.9389   0.0599
  -8.000  -0.2252   0.06878   0.06389  -0.0872   0.9278   0.0605
  -7.750  -0.2062   0.06602   0.06108  -0.0884   0.9143   0.0585
  -7.500  -0.1959   0.06159   0.05658  -0.0924   0.8984   0.0569
  -7.000  -0.2087   0.04602   0.03985  -0.1035   0.8624   0.0505
  -6.750  -0.1940   0.04303   0.03661  -0.1040   0.8488   0.0502
  -6.500  -0.1784   0.04013   0.03339  -0.1043   0.8355   0.0501
  -6.250  -0.1609   0.03744   0.03029  -0.1045   0.8230   0.0502
  -6.000  -0.1417   0.03496   0.02732  -0.1046   0.8114   0.0509
  -5.750  -0.1201   0.03300   0.02517  -0.1045   0.8000   0.0517
  -5.500  -0.0980   0.03123   0.02312  -0.1043   0.7883   0.0521
  -5.250  -0.0744   0.02943   0.02093  -0.1041   0.7781   0.0521
  -5.000  -0.0500   0.02789   0.01905  -0.1038   0.7677   0.0522
  -4.750  -0.0253   0.02657   0.01745  -0.1035   0.7569   0.0525
  -4.500   0.0006   0.02538   0.01598  -0.1032   0.7476   0.0529
  -4.250   0.0260   0.02435   0.01474  -0.1028   0.7370   0.0535
  -4.000   0.0521   0.02345   0.01365  -0.1025   0.7278   0.0544
  -3.750   0.0784   0.02271   0.01274  -0.1022   0.7186   0.0560
  -3.500   0.1046   0.02203   0.01189  -0.1018   0.7093   0.0577
  -3.250   0.1312   0.02135   0.01103  -0.1014   0.7008   0.0587
  -3.000   0.1572   0.02076   0.01033  -0.1009   0.6918   0.0595
  -2.750   0.1831   0.02013   0.00965  -0.1005   0.6841   0.0605
  -2.500   0.2082   0.01959   0.00913  -0.1000   0.6759   0.0619
  -2.250   0.2339   0.01917   0.00867  -0.0996   0.6682   0.0636
  -2.000   0.2596   0.01886   0.00830  -0.0992   0.6607   0.0662
  -1.750   0.2857   0.01861   0.00795  -0.0989   0.6533   0.0701
  -1.500   0.3119   0.01831   0.00762  -0.0986   0.6470   0.0745
  -1.250   0.3380   0.01811   0.00737  -0.0983   0.6395   0.0796
  -1.000   0.3649   0.01787   0.00708  -0.0980   0.6337   0.0887
  -0.750   0.3908   0.01758   0.00690  -0.0977   0.6267   0.1177
  -0.500   0.4126   0.01626   0.00689  -0.0974   0.6207   0.4593
  -0.250   0.4347   0.01591   0.00702  -0.0958   0.6155   0.6305
   0.000   0.4549   0.01574   0.00718  -0.0937   0.6089   0.7374
   0.250   0.4771   0.01551   0.00715  -0.0916   0.6035   0.8382
   0.500   0.5316   0.01534   0.00698  -0.0964   0.5972   1.0000
   0.750   0.5571   0.01552   0.00701  -0.0962   0.5911   1.0000
   1.000   0.5839   0.01567   0.00697  -0.0961   0.5860   1.0000
   1.250   0.6097   0.01588   0.00706  -0.0959   0.5802   1.0000
   1.500   0.6357   0.01609   0.00716  -0.0957   0.5745   1.0000
   1.750   0.6628   0.01627   0.00719  -0.0956   0.5698   1.0000
   2.000   0.6886   0.01651   0.00735  -0.0953   0.5642   1.0000
   2.250   0.7145   0.01675   0.00752  -0.0951   0.5586   1.0000
   2.500   0.7416   0.01696   0.00761  -0.0950   0.5540   1.0000
   2.750   0.7674   0.01723   0.00783  -0.0947   0.5488   1.0000
   3.000   0.7928   0.01750   0.00808  -0.0944   0.5432   1.0000
   3.250   0.8196   0.01773   0.00823  -0.0943   0.5384   1.0000
   3.500   0.8458   0.01801   0.00846  -0.0941   0.5337   1.0000
   3.750   0.8703   0.01833   0.00881  -0.0937   0.5280   1.0000
   4.000   0.8965   0.01860   0.00903  -0.0934   0.5231   1.0000
   4.250   0.9238   0.01886   0.00923  -0.0934   0.5188   1.0000
   4.500   0.9467   0.01924   0.00969  -0.0928   0.5127   1.0000
   4.750   0.9721   0.01954   0.01000  -0.0924   0.5077   1.0000
   5.000   0.9995   0.01981   0.01022  -0.0924   0.5035   1.0000
   5.250   1.0219   0.02022   0.01073  -0.0917   0.4976   1.0000
   5.500   1.0461   0.02057   0.01112  -0.0912   0.4921   1.0000
   5.750   1.0728   0.02086   0.01140  -0.0911   0.4878   1.0000
   6.000   1.0954   0.02129   0.01193  -0.0904   0.4825   1.0000
   6.250   1.1181   0.02170   0.01243  -0.0898   0.4767   1.0000
   6.500   1.1439   0.02200   0.01274  -0.0895   0.4721   1.0000
   6.750   1.1665   0.02244   0.01327  -0.0888   0.4669   1.0000
   7.000   1.1876   0.02292   0.01388  -0.0880   0.4612   1.0000
   7.250   1.2125   0.02326   0.01426  -0.0876   0.4565   1.0000
   7.500   1.2352   0.02369   0.01479  -0.0870   0.4515   1.0000
   7.750   1.2541   0.02424   0.01550  -0.0858   0.4455   1.0000
   8.000   1.2780   0.02461   0.01594  -0.0853   0.4409   1.0000
   8.250   1.3004   0.02505   0.01649  -0.0846   0.4362   1.0000
   8.500   1.3167   0.02566   0.01727  -0.0831   0.4295   1.0000
   8.750   1.3409   0.02587   0.01752  -0.0826   0.4239   1.0000
   9.000   1.3551   0.02648   0.01832  -0.0808   0.4167   1.0000
   9.250   1.3748   0.02676   0.01870  -0.0796   0.4096   1.0000
   9.500   1.3891   0.02728   0.01936  -0.0777   0.4021   1.0000
   9.750   1.4058   0.02756   0.01972  -0.0761   0.3939   1.0000
  10.000   1.4139   0.02811   0.02041  -0.0734   0.3841   1.0000
  10.250   1.4221   0.02842   0.02076  -0.0705   0.3732   1.0000
  10.500   1.4263   0.02888   0.02124  -0.0672   0.3604   1.0000
  10.750   1.4256   0.02968   0.02206  -0.0637   0.3461   1.0000
  11.000   1.4216   0.03087   0.02329  -0.0603   0.3302   1.0000
  11.250   1.4170   0.03238   0.02484  -0.0573   0.3146   1.0000
  11.500   1.4116   0.03423   0.02672  -0.0548   0.2989   1.0000
  11.750   1.4059   0.03638   0.02892  -0.0528   0.2833   1.0000
  12.000   1.3995   0.03885   0.03145  -0.0511   0.2674   1.0000
  12.250   1.3918   0.04167   0.03433  -0.0498   0.2505   1.0000
  12.500   1.3826   0.04485   0.03753  -0.0488   0.2319   1.0000
  12.750   1.3706   0.04848   0.04113  -0.0480   0.2117   1.0000
  13.000   1.3559   0.05261   0.04520  -0.0475   0.1891   1.0000
  13.250   1.3386   0.05727   0.04976  -0.0474   0.1678   1.0000
  13.500   1.3215   0.06220   0.05460  -0.0476   0.1487   1.0000
  13.750   1.3049   0.06728   0.05962  -0.0481   0.1330   1.0000
  14.000   1.2895   0.07246   0.06476  -0.0488   0.1189   1.0000
  14.250   1.2756   0.07762   0.06990  -0.0497   0.1057   1.0000
  14.500   1.2636   0.08268   0.07497  -0.0507   0.0927   1.0000
  14.750   1.2523   0.08780   0.08009  -0.0518   0.0800   1.0000
  15.000   1.2408   0.09306   0.08533  -0.0531   0.0692   1.0000
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