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GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 374 AIRFOIL (goe374-il)
Reynolds number: 50,000
Max Cl/Cd: 32.59 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe374-il-50000.txt
Download as CSV file: xf-goe374-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 374 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3749   0.11184   0.10505  -0.0125   1.0000   0.0907
  -8.500  -0.3792   0.11110   0.10443  -0.0149   1.0000   0.0931
  -8.250  -0.3838   0.11017   0.10362  -0.0170   1.0000   0.0937
  -8.000  -0.3634   0.10301   0.09640  -0.0146   1.0000   0.0996
  -7.750  -0.3619   0.10065   0.09413  -0.0152   1.0000   0.1037
  -7.500  -0.3659   0.09940   0.09301  -0.0175   1.0000   0.1063
  -7.250  -0.3679   0.09891   0.09260  -0.0231   1.0000   0.1075
  -7.000  -0.3533   0.09221   0.08596  -0.0174   1.0000   0.1140
  -6.750  -0.3507   0.09021   0.08403  -0.0201   1.0000   0.1195
  -6.500  -0.3475   0.08822   0.08212  -0.0243   1.0000   0.1223
  -6.250  -0.3387   0.08374   0.07771  -0.0206   1.0000   0.1307
  -6.000  -0.3335   0.08253   0.07652  -0.0267   1.0000   0.1362
  -5.750  -0.3266   0.07808   0.07217  -0.0225   1.0000   0.1462
  -5.250  -0.3123   0.07234   0.06652  -0.0247   1.0000   0.1666
  -4.750  -0.2980   0.06652   0.06077  -0.0235   1.0000   0.1965
  -4.500   0.0252   0.03932   0.03289  -0.0216   1.0000   1.0000
  -4.250   0.0357   0.03751   0.03115  -0.0223   1.0000   1.0000
  -4.000   0.0462   0.03580   0.02952  -0.0229   1.0000   1.0000
  -3.750   0.0562   0.03411   0.02790  -0.0234   1.0000   1.0000
  -3.500   0.0660   0.03256   0.02642  -0.0238   1.0000   1.0000
  -3.250  -0.1755   0.04377   0.03855   0.0248   1.0000   0.8280
  -2.500  -0.3232   0.04459   0.04010   0.0298   1.0000   0.6189
  -2.250  -0.3285   0.04243   0.03806   0.0372   1.0000   0.6652
  -2.000  -0.3298   0.04019   0.03590   0.0430   1.0000   0.7013
  -1.750  -0.3256   0.03810   0.03387   0.0449   1.0000   0.7246
  -1.500  -0.3131   0.03576   0.03157   0.0440   1.0000   0.7399
  -1.250  -0.2811   0.03325   0.02901   0.0374   1.0000   0.7386
  -1.000  -0.0261   0.03167   0.02437  -0.0317   1.0000   0.3167
  -0.750   0.0101   0.03130   0.02320  -0.0336   1.0000   0.2468
  -0.500   0.0354   0.03075   0.02220  -0.0337   1.0000   0.2123
  -0.250   0.1049   0.02973   0.02051  -0.0408   0.9826   0.1848
   0.000   0.1697   0.02905   0.01915  -0.0468   0.9612   0.1634
   0.250   0.2376   0.02793   0.01767  -0.0534   0.9416   0.1570
   0.500   0.2983   0.02714   0.01660  -0.0587   0.9187   0.1596
   0.750   0.3650   0.02623   0.01554  -0.0648   0.8986   0.1611
   1.000   0.4174   0.02560   0.01484  -0.0686   0.8749   0.1685
   1.250   0.4741   0.02469   0.01411  -0.0728   0.8542   0.2086
   1.500   0.5334   0.02261   0.01357  -0.0772   0.8317   1.0000
   1.750   0.5733   0.02263   0.01320  -0.0778   0.8092   1.0000
   2.000   0.6072   0.02271   0.01298  -0.0775   0.7867   1.0000
   2.250   0.6362   0.02294   0.01299  -0.0767   0.7645   1.0000
   2.500   0.6655   0.02311   0.01298  -0.0758   0.7439   1.0000
   2.750   0.6920   0.02342   0.01318  -0.0747   0.7237   1.0000
   3.000   0.7174   0.02382   0.01346  -0.0735   0.7038   1.0000
   3.250   0.7443   0.02411   0.01363  -0.0724   0.6859   1.0000
   3.500   0.7683   0.02467   0.01413  -0.0712   0.6673   1.0000
   3.750   0.7918   0.02530   0.01472  -0.0699   0.6486   1.0000
   4.000   0.8163   0.02589   0.01531  -0.0687   0.6310   1.0000
   4.250   0.8413   0.02644   0.01580  -0.0674   0.6137   1.0000
   4.500   0.8624   0.02728   0.01667  -0.0661   0.5941   1.0000
   4.750   0.8853   0.02782   0.01719  -0.0644   0.5737   1.0000
   5.000   0.9086   0.02828   0.01768  -0.0627   0.5534   1.0000
   5.250   0.9299   0.02892   0.01836  -0.0611   0.5322   1.0000
   5.500   0.9547   0.02929   0.01869  -0.0596   0.5133   1.0000
   5.750   0.9745   0.03017   0.01969  -0.0581   0.4926   1.0000
   6.000   0.9979   0.03075   0.02029  -0.0566   0.4729   1.0000
   6.250   1.0195   0.03159   0.02125  -0.0551   0.4528   1.0000
   6.500   1.0403   0.03265   0.02243  -0.0537   0.4326   1.0000
   6.750   1.0647   0.03345   0.02321  -0.0524   0.4135   1.0000
   7.000   1.0810   0.03503   0.02503  -0.0508   0.3929   1.0000
   7.250   1.1011   0.03636   0.02648  -0.0494   0.3748   1.0000
   7.500   1.1200   0.03807   0.02844  -0.0482   0.3598   1.0000
   7.750   1.1367   0.04003   0.03065  -0.0470   0.3462   1.0000
   8.000   1.1517   0.04214   0.03304  -0.0457   0.3341   1.0000
   8.250   1.1683   0.04413   0.03527  -0.0445   0.3237   1.0000
   8.500   1.1888   0.04529   0.03660  -0.0433   0.3116   1.0000
   8.750   1.2186   0.04235   0.03353  -0.0411   0.2840   1.0000
   9.000   1.2376   0.04288   0.03427  -0.0395   0.2700   1.0000
   9.250   1.2527   0.04298   0.03464  -0.0375   0.2524   1.0000
   9.500   1.2711   0.04096   0.03259  -0.0350   0.2258   1.0000
   9.750   1.2759   0.03985   0.03153  -0.0316   0.1949   1.0000
  10.000   1.2728   0.04029   0.03182  -0.0277   0.1615   1.0000
  10.250   1.2616   0.04282   0.03424  -0.0239   0.1301   1.0000
  10.500   1.2537   0.04557   0.03682  -0.0207   0.1096   1.0000
  10.750   1.2494   0.04840   0.03971  -0.0180   0.0974   1.0000
  11.000   1.2480   0.05153   0.04300  -0.0158   0.0890   1.0000
  11.250   1.2539   0.05433   0.04568  -0.0141   0.0822   1.0000
  11.500   1.2511   0.05821   0.05000  -0.0126   0.0789   1.0000
  11.750   1.2464   0.06215   0.05424  -0.0115   0.0764   1.0000
  12.000   1.2403   0.06626   0.05859  -0.0109   0.0744   1.0000
  12.250   1.2312   0.07077   0.06333  -0.0110   0.0735   1.0000
  12.500   1.2177   0.07587   0.06865  -0.0119   0.0728   1.0000
  12.750   1.1843   0.08378   0.07692  -0.0159   0.0748   1.0000
  13.000   1.1469   0.09358   0.08696  -0.0221   0.0776   1.0000
  13.250   1.1154   0.10372   0.09722  -0.0283   0.0799   1.0000
  13.500   1.0910   0.11342   0.10690  -0.0338   0.0815   1.0000
  13.750   1.0712   0.12286   0.11634  -0.0388   0.0825   1.0000
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