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GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 436 AIRFOIL (goe436-il)
Reynolds number: 100,000
Max Cl/Cd: 51.65 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe436-il-100000-n5.txt
Download as CSV file: xf-goe436-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 436 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3582   0.09260   0.08746  -0.0388   1.0000   0.0587
  -8.750  -0.3659   0.08945   0.08438  -0.0391   1.0000   0.0589
  -8.500  -0.3766   0.08648   0.08150  -0.0389   1.0000   0.0589
  -8.250  -0.3890   0.08395   0.07906  -0.0377   1.0000   0.0586
  -8.000  -0.4065   0.08166   0.07687  -0.0358   1.0000   0.0583
  -7.750  -0.4206   0.07891   0.07420  -0.0349   1.0000   0.0579
  -7.500  -0.4345   0.07590   0.07123  -0.0342   1.0000   0.0575
  -7.250  -0.4259   0.07000   0.06525  -0.0406   0.9944   0.0575
  -7.000  -0.4095   0.06219   0.05719  -0.0498   0.9856   0.0588
  -6.750  -0.3937   0.05494   0.04955  -0.0562   0.9769   0.0595
  -6.500  -0.3752   0.04891   0.04310  -0.0604   0.9696   0.0597
  -6.250  -0.3557   0.04372   0.03740  -0.0633   0.9622   0.0611
  -6.000  -0.3290   0.04242   0.03612  -0.0645   0.9570   0.0626
  -5.750  -0.3051   0.04002   0.03351  -0.0656   0.9501   0.0637
  -5.500  -0.2757   0.03688   0.02998  -0.0678   0.9455   0.0644
  -5.250  -0.2545   0.03449   0.02727  -0.0678   0.9371   0.0653
  -5.000  -0.2225   0.03229   0.02469  -0.0695   0.9317   0.0672
  -4.750  -0.1952   0.03034   0.02234  -0.0700   0.9231   0.0693
  -4.500  -0.1601   0.02823   0.01978  -0.0716   0.9164   0.0706
  -4.250  -0.1291   0.02659   0.01772  -0.0722   0.9075   0.0718
  -4.000  -0.0924   0.02502   0.01584  -0.0738   0.9001   0.0734
  -3.750  -0.0628   0.02396   0.01474  -0.0742   0.8896   0.0757
  -3.500  -0.0253   0.02292   0.01356  -0.0758   0.8829   0.0782
  -3.250   0.0020   0.02204   0.01254  -0.0755   0.8720   0.0800
  -3.000   0.0341   0.02115   0.01150  -0.0760   0.8637   0.0821
  -2.750   0.0658   0.02041   0.01060  -0.0763   0.8545   0.0848
  -2.500   0.0949   0.01969   0.00982  -0.0763   0.8440   0.0878
  -2.250   0.1279   0.01897   0.00912  -0.0770   0.8354   0.0911
  -2.000   0.1556   0.01843   0.00856  -0.0767   0.8233   0.0939
  -1.750   0.1836   0.01794   0.00804  -0.0763   0.8111   0.0974
  -1.500   0.2122   0.01750   0.00755  -0.0761   0.7990   0.1020
  -1.250   0.2403   0.01704   0.00713  -0.0758   0.7862   0.1079
  -1.000   0.2673   0.01670   0.00674  -0.0753   0.7719   0.1135
  -0.750   0.2929   0.01637   0.00640  -0.0745   0.7561   0.1200
  -0.500   0.3189   0.01611   0.00611  -0.0738   0.7394   0.1315
  -0.250   0.3442   0.01581   0.00587  -0.0730   0.7211   0.1495
   0.000   0.3702   0.01539   0.00562  -0.0724   0.7021   0.1948
   0.500   0.4850   0.01324   0.00537  -0.0832   0.6569   1.0000
   0.750   0.5084   0.01336   0.00525  -0.0820   0.6353   1.0000
   1.000   0.5317   0.01353   0.00519  -0.0809   0.6147   1.0000
   1.250   0.5544   0.01372   0.00518  -0.0796   0.5943   1.0000
   1.500   0.5767   0.01392   0.00523  -0.0784   0.5740   1.0000
   1.750   0.5990   0.01415   0.00529  -0.0771   0.5542   1.0000
   2.000   0.6213   0.01438   0.00536  -0.0759   0.5356   1.0000
   2.250   0.6438   0.01463   0.00546  -0.0747   0.5186   1.0000
   2.500   0.6665   0.01488   0.00558  -0.0736   0.5037   1.0000
   2.750   0.6894   0.01515   0.00572  -0.0726   0.4905   1.0000
   3.000   0.7126   0.01543   0.00590  -0.0716   0.4788   1.0000
   3.250   0.7359   0.01573   0.00607  -0.0707   0.4686   1.0000
   3.500   0.7594   0.01604   0.00630  -0.0698   0.4586   1.0000
   3.750   0.7832   0.01636   0.00655  -0.0690   0.4503   1.0000
   4.000   0.8071   0.01668   0.00683  -0.0682   0.4425   1.0000
   4.250   0.8313   0.01704   0.00711  -0.0675   0.4355   1.0000
   4.500   0.8552   0.01738   0.00746  -0.0668   0.4280   1.0000
   4.750   0.8799   0.01777   0.00776  -0.0662   0.4221   1.0000
   5.000   0.9038   0.01812   0.00816  -0.0655   0.4154   1.0000
   5.250   0.9281   0.01850   0.00854  -0.0648   0.4092   1.0000
   5.500   0.9525   0.01891   0.00894  -0.0642   0.4035   1.0000
   5.750   0.9761   0.01930   0.00939  -0.0635   0.3971   1.0000
   6.000   1.0002   0.01971   0.00977  -0.0628   0.3905   1.0000
   6.250   1.0211   0.02005   0.01020  -0.0616   0.3807   1.0000
   6.500   1.0423   0.02039   0.01052  -0.0605   0.3709   1.0000
   6.750   1.0625   0.02070   0.01088  -0.0592   0.3604   1.0000
   7.000   1.0829   0.02105   0.01130  -0.0579   0.3509   1.0000
   7.250   1.1041   0.02141   0.01169  -0.0568   0.3433   1.0000
   7.500   1.1256   0.02181   0.01221  -0.0558   0.3365   1.0000
   7.750   1.1466   0.02220   0.01269  -0.0547   0.3296   1.0000
   8.000   1.1673   0.02261   0.01319  -0.0535   0.3229   1.0000
   8.250   1.1865   0.02300   0.01371  -0.0522   0.3144   1.0000
   8.500   1.2045   0.02338   0.01418  -0.0506   0.3050   1.0000
   8.750   1.2217   0.02376   0.01463  -0.0489   0.2955   1.0000
   9.000   1.2392   0.02420   0.01525  -0.0473   0.2862   1.0000
   9.250   1.2559   0.02465   0.01577  -0.0456   0.2781   1.0000
   9.500   1.2718   0.02513   0.01643  -0.0439   0.2682   1.0000
   9.750   1.2857   0.02562   0.01705  -0.0418   0.2569   1.0000
  10.000   1.2966   0.02615   0.01769  -0.0393   0.2436   1.0000
  10.250   1.3056   0.02676   0.01838  -0.0365   0.2300   1.0000
  10.500   1.3131   0.02748   0.01916  -0.0337   0.2144   1.0000
  10.750   1.3182   0.02837   0.02007  -0.0308   0.1972   1.0000
  11.000   1.3210   0.02949   0.02117  -0.0279   0.1806   1.0000
  11.250   1.3210   0.03089   0.02253  -0.0250   0.1648   1.0000
  11.500   1.3192   0.03255   0.02418  -0.0223   0.1499   1.0000
  11.750   1.3151   0.03453   0.02615  -0.0198   0.1362   1.0000
  12.000   1.3099   0.03675   0.02838  -0.0176   0.1237   1.0000
  12.250   1.3046   0.03918   0.03085  -0.0159   0.1125   1.0000
  12.500   1.2983   0.04187   0.03358  -0.0145   0.1033   1.0000
  12.750   1.2892   0.04502   0.03676  -0.0135   0.0955   1.0000
  13.000   1.2836   0.04808   0.03992  -0.0130   0.0880   1.0000
  13.250   1.2738   0.05179   0.04368  -0.0130   0.0827   1.0000
  13.500   1.2655   0.05558   0.04758  -0.0132   0.0786   1.0000
  13.750   1.2547   0.05988   0.05195  -0.0139   0.0753   1.0000
  14.000   1.2435   0.06442   0.05655  -0.0149   0.0728   1.0000
  14.250   1.2351   0.06875   0.06100  -0.0159   0.0701   1.0000
  14.500   1.2251   0.07345   0.06580  -0.0172   0.0674   1.0000
  14.750   1.2153   0.07821   0.07061  -0.0186   0.0651   1.0000
  15.000   1.2070   0.08273   0.07515  -0.0198   0.0627   1.0000
  15.250   1.2027   0.08684   0.07942  -0.0210   0.0598   1.0000
  15.500   1.1976   0.09107   0.08375  -0.0222   0.0571   1.0000
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