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GOE 575 AIRFOIL (goe575-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 575 AIRFOIL (goe575-il)
Reynolds number: 50,000
Max Cl/Cd: 31.62 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe575-il-50000.txt
Download as CSV file: xf-goe575-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 575 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4447   0.11391   0.10694  -0.0121   1.0000   0.2809
  -8.000  -0.3977   0.10823   0.10118  -0.0100   1.0000   0.2922
  -7.750  -0.4505   0.10818   0.10134  -0.0089   1.0000   0.2997
  -7.500  -0.4073   0.10316   0.09625  -0.0070   1.0000   0.3137
  -7.250  -0.4234   0.10066   0.09387  -0.0053   1.0000   0.3223
  -7.000  -0.4299   0.09860   0.09187  -0.0030   1.0000   0.3354
  -6.750  -0.4188   0.09517   0.08848  -0.0012   1.0000   0.3458
  -6.500  -0.4822   0.09515   0.08868   0.0042   1.0000   0.3564
  -6.250  -0.4611   0.09147   0.08502   0.0058   1.0000   0.3740
  -6.000  -0.4528   0.08851   0.08211   0.0085   1.0000   0.3913
  -5.750  -0.4624   0.08644   0.08013   0.0128   1.0000   0.4107
  -5.500  -0.4797   0.08476   0.07857   0.0181   1.0000   0.4307
  -5.250  -0.4529   0.08174   0.07557   0.0206   1.0000   0.4664
  -5.000  -0.4352   0.07929   0.07315   0.0240   1.0000   0.5028
  -4.750  -0.3978   0.07693   0.07079   0.0269   1.0000   0.5568
  -3.750  -0.6313   0.05779   0.04983   0.0337   1.0000   0.2077
  -3.500  -0.6231   0.05524   0.04728   0.0364   1.0000   0.2022
  -3.250  -0.6321   0.05252   0.04373   0.0425   1.0000   0.1887
  -3.000  -0.6259   0.05038   0.04151   0.0457   1.0000   0.1871
  -2.750  -0.6221   0.04869   0.03958   0.0495   1.0000   0.1867
  -2.500  -0.6168   0.04704   0.03768   0.0531   1.0000   0.1861
  -2.250  -0.6114   0.04570   0.03601   0.0568   1.0000   0.1869
  -2.000  -0.6043   0.04438   0.03434   0.0603   1.0000   0.1876
  -1.750  -0.5945   0.04313   0.03279   0.0632   1.0000   0.1880
  -1.500  -0.5828   0.04196   0.03129   0.0657   1.0000   0.1891
  -1.250  -0.5669   0.04073   0.03002   0.0669   1.0000   0.1920
  -1.000  -0.5521   0.04005   0.02931   0.0682   1.0000   0.1983
  -0.750  -0.5340   0.03933   0.02831   0.0692   1.0000   0.2035
  -0.500  -0.4984   0.03879   0.02756   0.0664   0.9969   0.2114
  -0.250  -0.2708   0.03835   0.02718   0.0260   0.9591   0.3168
   0.000  -0.1121   0.03724   0.02740  -0.0014   0.9423   0.4929
   0.250   0.1181   0.04002   0.03076  -0.0405   0.9338   1.0000
   0.500   0.1631   0.03999   0.03050  -0.0444   0.9122   1.0000
   0.750   0.2169   0.03995   0.03025  -0.0496   0.8936   1.0000
   1.000   0.2596   0.03985   0.02999  -0.0526   0.8741   1.0000
   1.250   0.2998   0.03967   0.02969  -0.0551   0.8537   1.0000
   1.500   0.3435   0.03936   0.02928  -0.0578   0.8348   1.0000
   1.750   0.3878   0.03895   0.02878  -0.0604   0.8167   1.0000
   2.000   0.4333   0.03837   0.02813  -0.0629   0.7991   1.0000
   2.250   0.4781   0.03773   0.02744  -0.0651   0.7825   1.0000
   2.500   0.5254   0.03685   0.02651  -0.0674   0.7666   1.0000
   2.750   0.5791   0.03569   0.02533  -0.0706   0.7519   1.0000
   3.000   0.6747   0.03300   0.02259  -0.0804   0.7413   1.0000
   3.250   0.7438   0.03186   0.02143  -0.0868   0.7221   1.0000
   3.500   0.7980   0.03154   0.02108  -0.0910   0.6990   1.0000
   3.750   0.8776   0.03095   0.02040  -0.0999   0.6729   1.0000
   4.000   0.9410   0.03084   0.02018  -0.1060   0.6472   1.0000
   4.250   0.9662   0.03146   0.02077  -0.1052   0.6266   1.0000
   4.500   0.9929   0.03211   0.02140  -0.1048   0.6075   1.0000
   4.750   1.0186   0.03275   0.02202  -0.1041   0.5894   1.0000
   5.000   1.0440   0.03340   0.02264  -0.1033   0.5722   1.0000
   5.250   1.0702   0.03407   0.02327  -0.1027   0.5555   1.0000
   5.500   1.0980   0.03472   0.02388  -0.1024   0.5391   1.0000
   5.750   1.0976   0.03587   0.02515  -0.0970   0.5253   1.0000
   6.000   1.1063   0.03697   0.02630  -0.0933   0.5116   1.0000
   6.250   1.1242   0.03785   0.02720  -0.0912   0.4972   1.0000
   6.500   1.1500   0.03863   0.02796  -0.0906   0.4827   1.0000
   6.750   1.1588   0.03981   0.02921  -0.0870   0.4700   1.0000
   7.000   1.1549   0.04139   0.03092  -0.0813   0.4590   1.0000
   7.250   1.1799   0.04233   0.03185  -0.0806   0.4464   1.0000
   7.500   1.1780   0.04387   0.03352  -0.0754   0.4358   1.0000
   7.750   1.1790   0.04552   0.03526  -0.0709   0.4261   1.0000
   8.000   1.2101   0.04633   0.03606  -0.0712   0.4143   1.0000
   8.250   1.1768   0.04906   0.03901  -0.0614   0.4083   1.0000
   8.500   1.2223   0.04929   0.03918  -0.0639   0.3947   1.0000
   8.750   1.1688   0.05262   0.04273  -0.0514   0.3913   1.0000
   9.000   1.1065   0.05649   0.04675  -0.0389   0.3888   1.0000
   9.250   0.9825   0.06619   0.05655  -0.0246   0.3900   1.0000
   9.500   0.8014   0.08975   0.07996  -0.0236   0.3923   1.0000
   9.750   0.7590   0.09848   0.08867  -0.0246   0.3907   1.0000
  10.000   0.7375   0.10488   0.09509  -0.0253   0.3904   1.0000
  10.250   0.7230   0.11052   0.10077  -0.0260   0.3905   1.0000
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