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GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 429 AIRFOIL (goe429-il)
Reynolds number: 100,000
Max Cl/Cd: 35.54 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe429-il-100000.txt
Download as CSV file: xf-goe429-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 429 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.9074   0.09431   0.08937   0.0117   1.0000   0.0738
 -12.000  -0.9377   0.08407   0.07907   0.0049   1.0000   0.0728
 -11.750  -0.9732   0.07448   0.06935  -0.0021   1.0000   0.0714
 -11.500  -1.0089   0.06658   0.06123  -0.0074   1.0000   0.0701
 -11.250  -1.0393   0.06087   0.05524  -0.0092   1.0000   0.0696
 -11.000  -1.0563   0.05600   0.04999  -0.0095   1.0000   0.0702
 -10.750  -1.0653   0.05144   0.04496  -0.0093   1.0000   0.0716
 -10.500  -1.0687   0.04716   0.04004  -0.0086   1.0000   0.0735
 -10.250  -1.0594   0.04336   0.03597  -0.0082   1.0000   0.0763
 -10.000  -1.0405   0.04167   0.03426  -0.0078   1.0000   0.0812
  -9.750  -1.0301   0.03912   0.03097  -0.0069   1.0000   0.0864
  -9.500  -1.0090   0.03653   0.02858  -0.0067   1.0000   0.0926
  -9.250  -0.9919   0.03437   0.02590  -0.0061   1.0000   0.1002
  -9.000  -0.9694   0.03255   0.02420  -0.0059   1.0000   0.1083
  -8.750  -0.9480   0.03059   0.02205  -0.0055   1.0000   0.1167
  -8.500  -0.9254   0.02934   0.02058  -0.0052   1.0000   0.1261
  -8.250  -0.9013   0.02790   0.01926  -0.0050   1.0000   0.1349
  -8.000  -0.8772   0.02654   0.01772  -0.0047   1.0000   0.1440
  -7.750  -0.8520   0.02550   0.01662  -0.0045   1.0000   0.1531
  -7.500  -0.8264   0.02437   0.01554  -0.0043   1.0000   0.1618
  -7.250  -0.8005   0.02330   0.01434  -0.0040   1.0000   0.1717
  -7.000  -0.7744   0.02242   0.01343  -0.0038   1.0000   0.1827
  -6.750  -0.7483   0.02144   0.01254  -0.0036   1.0000   0.1945
  -6.500  -0.7222   0.02051   0.01164  -0.0034   1.0000   0.2092
  -6.250  -0.6961   0.01957   0.01074  -0.0033   1.0000   0.2283
  -6.000  -0.6705   0.01858   0.00995  -0.0030   1.0000   0.2532
  -5.750  -0.6452   0.01770   0.00928  -0.0028   1.0000   0.2882
  -5.500  -0.6192   0.01707   0.00879  -0.0026   1.0000   0.3260
  -5.250  -0.5928   0.01664   0.00847  -0.0023   1.0000   0.3586
  -5.000  -0.5659   0.01630   0.00819  -0.0021   1.0000   0.3877
  -4.750  -0.5389   0.01597   0.00798  -0.0019   1.0000   0.4131
  -4.500  -0.5115   0.01566   0.00771  -0.0017   1.0000   0.4392
  -4.250  -0.4843   0.01536   0.00752  -0.0015   1.0000   0.4641
  -4.000  -0.4570   0.01508   0.00733  -0.0013   1.0000   0.4894
  -3.750  -0.4298   0.01484   0.00719  -0.0010   1.0000   0.5157
  -3.500  -0.4032   0.01469   0.00719  -0.0005   1.0000   0.5413
  -3.250  -0.3767   0.01462   0.00723  -0.0001   1.0000   0.5685
  -3.000  -0.3512   0.01462   0.00737   0.0006   1.0000   0.5923
  -2.750  -0.3268   0.01460   0.00742   0.0012   1.0000   0.6158
  -2.500  -0.3062   0.01463   0.00755   0.0024   1.0000   0.6350
  -2.250  -0.2875   0.01466   0.00764   0.0036   1.0000   0.6534
  -2.000  -0.2685   0.01469   0.00772   0.0046   1.0000   0.6717
  -1.750  -0.2486   0.01473   0.00780   0.0054   1.0000   0.6900
  -1.500  -0.2062   0.01474   0.00781   0.0022   0.9894   0.7122
  -1.250  -0.1562   0.01470   0.00787  -0.0018   0.9751   0.7324
  -1.000  -0.1076   0.01463   0.00787  -0.0054   0.9595   0.7529
  -0.750  -0.0648   0.01456   0.00784  -0.0075   0.9411   0.7732
  -0.500  -0.0334   0.01451   0.00783  -0.0073   0.9197   0.7927
  -0.250  -0.0093   0.01447   0.00785  -0.0053   0.8984   0.8113
   0.000   0.0107   0.01444   0.00787  -0.0022   0.8785   0.8316
   0.250   0.0289   0.01439   0.00786   0.0011   0.8579   0.8542
   0.500   0.0471   0.01430   0.00782   0.0044   0.8369   0.8768
   0.750   0.0674   0.01419   0.00772   0.0074   0.8161   0.8988
   1.000   0.0915   0.01405   0.00757   0.0095   0.7947   0.9211
   1.250   0.1238   0.01393   0.00744   0.0098   0.7690   0.9419
   1.500   0.1629   0.01382   0.00727   0.0086   0.7415   0.9615
   1.750   0.2066   0.01372   0.00711   0.0063   0.7096   0.9801
   2.000   0.2550   0.01361   0.00691   0.0027   0.6704   0.9971
   2.250   0.2770   0.01345   0.00665   0.0033   0.6346   1.0000
   2.500   0.2946   0.01336   0.00643   0.0047   0.5938   1.0000
   2.750   0.3164   0.01341   0.00625   0.0056   0.5441   1.0000
   3.000   0.3411   0.01368   0.00618   0.0061   0.4899   1.0000
   3.250   0.3670   0.01419   0.00632   0.0063   0.4416   1.0000
   3.500   0.3936   0.01481   0.00661   0.0064   0.4050   1.0000
   3.750   0.4210   0.01542   0.00701   0.0063   0.3761   1.0000
   4.000   0.4486   0.01604   0.00747   0.0062   0.3538   1.0000
   4.250   0.4763   0.01658   0.00791   0.0061   0.3335   1.0000
   4.500   0.5037   0.01706   0.00828   0.0061   0.3144   1.0000
   4.750   0.5311   0.01753   0.00869   0.0060   0.2978   1.0000
   5.000   0.5587   0.01804   0.00918   0.0060   0.2846   1.0000
   5.250   0.5861   0.01853   0.00965   0.0059   0.2720   1.0000
   5.500   0.6133   0.01902   0.01008   0.0059   0.2600   1.0000
   5.750   0.6404   0.01939   0.01049   0.0059   0.2464   1.0000
   6.000   0.6672   0.01971   0.01085   0.0060   0.2306   1.0000
   6.250   0.6936   0.02006   0.01124   0.0060   0.2137   1.0000
   6.500   0.7199   0.02034   0.01169   0.0060   0.1888   1.0000
   6.750   0.7446   0.02095   0.01219   0.0061   0.1536   1.0000
   7.000   0.7692   0.02197   0.01311   0.0064   0.1269   1.0000
   7.250   0.7939   0.02312   0.01421   0.0068   0.1142   1.0000
   7.500   0.8185   0.02438   0.01546   0.0072   0.1068   1.0000
   7.750   0.8432   0.02551   0.01660   0.0076   0.1008   1.0000
   8.000   0.8674   0.02688   0.01798   0.0079   0.0961   1.0000
   8.250   0.8919   0.02827   0.01955   0.0084   0.0920   1.0000
   8.500   0.9159   0.02975   0.02110   0.0088   0.0891   1.0000
   8.750   0.9397   0.03146   0.02278   0.0091   0.0868   1.0000
   9.000   0.9617   0.03366   0.02525   0.0096   0.0848   1.0000
   9.250   0.9815   0.03592   0.02790   0.0100   0.0825   1.0000
   9.500   0.9995   0.03847   0.03080   0.0105   0.0808   1.0000
   9.750   1.0145   0.04154   0.03424   0.0110   0.0798   1.0000
  10.000   1.0261   0.04485   0.03791   0.0114   0.0789   1.0000
  10.250   1.0372   0.04790   0.04122   0.0118   0.0777   1.0000
  10.500   1.0484   0.05079   0.04426   0.0121   0.0763   1.0000
  10.750   1.0517   0.05485   0.04856   0.0123   0.0755   1.0000
  11.000   1.0337   0.06031   0.05453   0.0120   0.0760   1.0000
  11.250   0.8384   0.09555   0.09058  -0.0151   0.0873   1.0000
  11.500   0.8469   0.09777   0.09278  -0.0145   0.0865   1.0000
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