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GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 518 AIRFOIL (goe518-il)
Reynolds number: 50,000
Max Cl/Cd: 23.75 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe518-il-50000-n5.txt
Download as CSV file: xf-goe518-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 518 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.0555   0.10799   0.10178  -0.0746   0.8832   0.1475
  -7.750  -0.0587   0.10550   0.09932  -0.0762   0.8734   0.1523
  -7.500  -0.1009   0.10455   0.09841  -0.0782   0.8598   0.1555
  -7.250  -0.1049   0.10129   0.09520  -0.0776   0.8477   0.1570
  -7.000  -0.0562   0.09638   0.09027  -0.0784   0.8446   0.1620
  -6.750  -0.0655   0.09435   0.08827  -0.0761   0.8309   0.1642
  -6.500  -0.0722   0.09188   0.08580  -0.0753   0.8186   0.1669
  -6.000  -0.1140   0.07723   0.07037  -0.0813   0.7944   0.0853
  -5.750  -0.1054   0.07486   0.06801  -0.0795   0.7837   0.0842
  -5.500  -0.0914   0.07153   0.06457  -0.0794   0.7756   0.0827
  -5.250  -0.0909   0.06905   0.06195  -0.0771   0.7633   0.0818
  -5.000  -0.0746   0.06534   0.05799  -0.0773   0.7565   0.0815
  -4.750  -0.0734   0.06321   0.05567  -0.0745   0.7435   0.0813
  -4.500  -0.0517   0.05965   0.05178  -0.0746   0.7379   0.0810
  -4.250  -0.0487   0.05774   0.04965  -0.0716   0.7246   0.0804
  -4.000  -0.0234   0.05422   0.04570  -0.0714   0.7196   0.0792
  -3.750  -0.0181   0.05256   0.04374  -0.0683   0.7064   0.0785
  -3.500   0.0031   0.05000   0.04076  -0.0670   0.6988   0.0779
  -3.250   0.0196   0.04816   0.03858  -0.0650   0.6886   0.0778
  -3.000   0.0429   0.04637   0.03649  -0.0639   0.6803   0.0786
  -2.750   0.0648   0.04488   0.03474  -0.0625   0.6707   0.0800
  -2.500   0.0911   0.04324   0.03276  -0.0617   0.6625   0.0815
  -2.250   0.1156   0.04184   0.03102  -0.0605   0.6529   0.0822
  -2.000   0.1508   0.04000   0.02879  -0.0607   0.6464   0.0830
  -1.750   0.1726   0.03912   0.02764  -0.0592   0.6350   0.0837
  -1.500   0.2166   0.03731   0.02540  -0.0606   0.6292   0.0854
  -1.250   0.2353   0.03695   0.02499  -0.0590   0.6164   0.0871
  -1.000   0.2775   0.03568   0.02353  -0.0606   0.6091   0.0913
  -0.750   0.3040   0.03533   0.02297  -0.0600   0.5972   0.0944
  -0.500   0.3509   0.03437   0.02179  -0.0627   0.5884   0.0980
  -0.250   0.3801   0.03405   0.02135  -0.0627   0.5773   0.1024
   0.000   0.4114   0.03367   0.02077  -0.0629   0.5676   0.1093
   0.250   0.4386   0.03336   0.02039  -0.0626   0.5577   0.1185
   0.500   0.4647   0.03310   0.02004  -0.0621   0.5485   0.1302
   0.750   0.4888   0.03286   0.01979  -0.0614   0.5393   0.1540
   1.000   0.6496   0.03076   0.01976  -0.0865   0.5257   1.0000
   1.250   0.6768   0.03092   0.01956  -0.0862   0.5181   1.0000
   1.500   0.6879   0.03151   0.01998  -0.0836   0.5100   1.0000
   1.750   0.7062   0.03195   0.02020  -0.0820   0.5028   1.0000
   2.000   0.7368   0.03212   0.02005  -0.0823   0.4970   1.0000
   2.250   0.7386   0.03301   0.02090  -0.0784   0.4893   1.0000
   2.500   0.7612   0.03338   0.02106  -0.0776   0.4834   1.0000
   2.750   0.7869   0.03372   0.02117  -0.0773   0.4781   1.0000
   3.000   0.7875   0.03475   0.02218  -0.0733   0.4714   1.0000
   3.250   0.8075   0.03526   0.02254  -0.0722   0.4662   1.0000
   3.500   0.8412   0.03542   0.02246  -0.0731   0.4622   1.0000
   3.750   0.8377   0.03674   0.02381  -0.0688   0.4568   1.0000
   4.000   0.8427   0.03785   0.02491  -0.0659   0.4518   1.0000
   4.250   0.8629   0.03844   0.02537  -0.0649   0.4477   1.0000
   4.500   0.8954   0.03864   0.02537  -0.0656   0.4444   1.0000
   4.750   0.8821   0.04052   0.02734  -0.0605   0.4393   1.0000
   5.000   0.8727   0.04244   0.02933  -0.0562   0.4341   1.0000
   5.250   0.8856   0.04344   0.03026  -0.0546   0.4303   1.0000
   5.500   0.9119   0.04385   0.03054  -0.0545   0.4275   1.0000
   5.750   0.9409   0.04422   0.03078  -0.0548   0.4252   1.0000
   6.000   0.8244   0.05329   0.04038  -0.0421   0.4157   1.0000
   6.250   0.8245   0.05559   0.04267  -0.0402   0.4117   1.0000
   6.500   0.8477   0.05605   0.04304  -0.0397   0.4094   1.0000
   6.750   0.8804   0.05582   0.04269  -0.0398   0.4077   1.0000
   7.250   0.7461   0.07493   0.06225  -0.0332   0.3899   1.0000
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