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GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 513 AIRFOIL (goe513-il)
Reynolds number: 50,000
Max Cl/Cd: 28.6 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe513-il-50000-n5.txt
Download as CSV file: xf-goe513-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 513 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3551   0.11255   0.10605  -0.0326   1.0000   0.0819
  -9.250  -0.3675   0.10855   0.10212  -0.0335   0.9988   0.0806
  -9.000  -0.3979   0.09778   0.09133  -0.0437   0.9911   0.0772
  -8.750  -0.3957   0.09270   0.08623  -0.0484   0.9834   0.0766
  -8.500  -0.4031   0.08752   0.08102  -0.0516   0.9743   0.0761
  -8.000  -0.4294   0.07554   0.06878  -0.0560   0.9543   0.0749
  -7.750  -0.4471   0.06951   0.06250  -0.0557   0.9424   0.0745
  -7.500  -0.4618   0.06444   0.05709  -0.0540   0.9316   0.0745
  -7.250  -0.4655   0.05947   0.05164  -0.0530   0.9234   0.0752
  -7.000  -0.4710   0.05594   0.04770  -0.0498   0.9126   0.0757
  -6.750  -0.4678   0.05258   0.04380  -0.0475   0.9038   0.0765
  -6.500  -0.4577   0.04973   0.04043  -0.0456   0.8951   0.0771
  -6.250  -0.4450   0.04769   0.03812  -0.0437   0.8860   0.0777
  -6.000  -0.4214   0.04583   0.03604  -0.0434   0.8782   0.0786
  -5.750  -0.4056   0.04435   0.03436  -0.0416   0.8681   0.0795
  -5.500  -0.3765   0.04268   0.03244  -0.0419   0.8611   0.0811
  -5.250  -0.3606   0.04152   0.03107  -0.0399   0.8499   0.0829
  -5.000  -0.3262   0.03996   0.02917  -0.0409   0.8436   0.0859
  -4.750  -0.3085   0.03897   0.02800  -0.0390   0.8314   0.0880
  -4.500  -0.2810   0.03794   0.02695  -0.0389   0.8220   0.0906
  -4.250  -0.2502   0.03688   0.02575  -0.0391   0.8128   0.0937
  -4.000  -0.2230   0.03602   0.02471  -0.0387   0.8020   0.0970
  -3.750  -0.1837   0.03493   0.02361  -0.0404   0.7943   0.1034
  -3.500  -0.1529   0.03423   0.02285  -0.0407   0.7829   0.1117
  -3.250  -0.1039   0.03314   0.02191  -0.0442   0.7763   0.1272
  -3.000  -0.0740   0.03265   0.02172  -0.0444   0.7647   0.1535
  -2.750  -0.0413   0.03225   0.02141  -0.0444   0.7571   0.2071
  -2.500  -0.0275   0.03241   0.02144  -0.0414   0.7436   0.2395
  -2.250   0.0036   0.03209   0.02086  -0.0409   0.7369   0.2705
  -2.000   0.0136   0.03229   0.02102  -0.0375   0.7226   0.2919
  -1.750   0.0367   0.03201   0.02067  -0.0359   0.7149   0.3249
  -1.500   0.0566   0.03194   0.02064  -0.0344   0.7023   0.3495
  -1.250   0.1056   0.03127   0.01981  -0.0378   0.6951   0.3691
  -1.000   0.1398   0.03115   0.01950  -0.0390   0.6831   0.3779
  -0.750   0.1906   0.03060   0.01884  -0.0430   0.6747   0.3876
  -0.500   0.2257   0.03042   0.01852  -0.0442   0.6635   0.3961
  -0.250   0.2611   0.03019   0.01825  -0.0455   0.6531   0.4044
   0.000   0.3007   0.02982   0.01778  -0.0474   0.6439   0.4158
   0.250   0.3242   0.02977   0.01776  -0.0467   0.6326   0.4260
   0.500   0.3659   0.02919   0.01715  -0.0488   0.6244   0.4409
   1.000   0.4171   0.02849   0.01673  -0.0478   0.6049   0.4928
   1.500   0.7179   0.02832   0.01700  -0.0932   0.5715   1.0000
   1.750   0.7320   0.02869   0.01724  -0.0908   0.5604   1.0000
   2.000   0.7583   0.02882   0.01712  -0.0903   0.5504   1.0000
   2.250   0.7754   0.02917   0.01735  -0.0884   0.5402   1.0000
   2.500   0.7986   0.02944   0.01743  -0.0876   0.5308   1.0000
   2.750   0.8160   0.02983   0.01771  -0.0857   0.5210   1.0000
   3.000   0.8386   0.03015   0.01788  -0.0848   0.5122   1.0000
   3.250   0.8517   0.03065   0.01832  -0.0823   0.5026   1.0000
   3.500   0.8768   0.03095   0.01846  -0.0818   0.4944   1.0000
   3.750   0.8826   0.03160   0.01913  -0.0781   0.4851   1.0000
   4.000   0.9110   0.03185   0.01920  -0.0782   0.4773   1.0000
   4.250   0.9105   0.03264   0.02006  -0.0735   0.4683   1.0000
   4.500   0.9292   0.03304   0.02036  -0.0719   0.4603   1.0000
   4.750   0.9376   0.03369   0.02100  -0.0687   0.4525   1.0000
   5.000   0.9455   0.03433   0.02164  -0.0655   0.4444   1.0000
   5.250   0.9686   0.03467   0.02184  -0.0647   0.4375   1.0000
   5.500   0.9603   0.03563   0.02290  -0.0588   0.4294   1.0000
   5.750   0.9770   0.03604   0.02324  -0.0570   0.4226   1.0000
   6.000   0.9781   0.03682   0.02404  -0.0528   0.4154   1.0000
   6.250   0.9789   0.03763   0.02488  -0.0486   0.4082   1.0000
   6.500   1.0050   0.03784   0.02496  -0.0482   0.4025   1.0000
   6.750   0.9898   0.03925   0.02649  -0.0420   0.3954   1.0000
   7.000   0.9971   0.04007   0.02732  -0.0391   0.3893   1.0000
   7.250   1.0267   0.04017   0.02729  -0.0392   0.3844   1.0000
   7.500   1.0016   0.04226   0.02956  -0.0324   0.3775   1.0000
   7.750   1.0090   0.04319   0.03049  -0.0298   0.3717   1.0000
   8.000   1.0390   0.04318   0.03036  -0.0299   0.3673   1.0000
   8.250   1.0046   0.04622   0.03361  -0.0231   0.3605   1.0000
   8.500   1.0057   0.04769   0.03512  -0.0203   0.3552   1.0000
   8.750   1.0303   0.04792   0.03528  -0.0198   0.3516   1.0000
   9.000   0.9973   0.05175   0.03927  -0.0147   0.3458   1.0000
   9.250   0.9605   0.05649   0.04416  -0.0105   0.3392   1.0000
   9.500   0.9793   0.05705   0.04469  -0.0095   0.3358   1.0000
   9.750   1.0188   0.05601   0.04358  -0.0096   0.3335   1.0000
  10.000   0.8764   0.07251   0.06044  -0.0051   0.3194   1.0000
  10.250   0.9039   0.07190   0.05980  -0.0041   0.3175   1.0000
  10.750   0.8149   0.09042   0.07853  -0.0053   0.3009   1.0000
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