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GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 495 AIRFOIL (goe495-il)
Reynolds number: 50,000
Max Cl/Cd: 44.75 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe495-il-50000.txt
Download as CSV file: xf-goe495-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 495 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3429   0.10225   0.09563  -0.0262   1.0000   0.1811
  -7.250  -0.3641   0.10296   0.09654  -0.0246   1.0000   0.1833
  -7.000  -0.3520   0.09813   0.09174  -0.0227   1.0000   0.1883
  -6.750  -0.3570   0.09643   0.09014  -0.0209   1.0000   0.1947
  -6.500  -0.3761   0.09709   0.09097  -0.0221   1.0000   0.1983
  -6.250  -0.3653   0.09226   0.08617  -0.0182   1.0000   0.2038
  -6.000  -0.3720   0.09103   0.08503  -0.0180   1.0000   0.2113
  -5.750  -0.3742   0.08852   0.08261  -0.0174   1.0000   0.2159
  -5.500  -0.3728   0.08620   0.08030  -0.0160   1.0000   0.2248
  -5.250  -0.3727   0.08359   0.07776  -0.0154   1.0000   0.2323
  -5.000  -0.3714   0.08176   0.07599  -0.0181   1.0000   0.2440
  -4.750  -0.3664   0.07944   0.07370  -0.0189   1.0000   0.2582
  -4.500  -0.3599   0.07686   0.07114  -0.0191   1.0000   0.2727
  -4.250  -0.3531   0.07398   0.06829  -0.0184   1.0000   0.2876
  -4.000  -0.3450   0.07108   0.06542  -0.0178   1.0000   0.3027
  -3.750  -0.3369   0.06815   0.06251  -0.0166   1.0000   0.3183
  -3.500  -0.3285   0.06531   0.05969  -0.0149   1.0000   0.3357
  -3.250  -0.3173   0.06275   0.05715  -0.0150   1.0000   0.3630
  -3.000  -0.3051   0.06075   0.05511  -0.0149   1.0000   0.4039
  -2.750  -0.1118   0.04163   0.03405  -0.0728   1.0000   0.1719
  -2.500  -0.0661   0.03745   0.02924  -0.0787   1.0000   0.1664
  -2.250  -0.0265   0.03417   0.02539  -0.0825   1.0000   0.1639
  -2.000   0.0107   0.03158   0.02215  -0.0852   1.0000   0.1646
  -1.750   0.0402   0.03008   0.02031  -0.0863   1.0000   0.1745
  -1.500   0.0697   0.02878   0.01856  -0.0871   1.0000   0.1862
  -1.250   0.0971   0.02774   0.01726  -0.0874   1.0000   0.2004
  -1.000   0.1232   0.02700   0.01647  -0.0875   1.0000   0.2308
  -0.750   0.1504   0.02633   0.01589  -0.0876   1.0000   0.2940
  -0.500   0.1739   0.02605   0.01590  -0.0871   1.0000   0.3946
  -0.250   0.1970   0.02573   0.01591  -0.0865   1.0000   0.4965
   0.000   0.2220   0.02486   0.01568  -0.0858   1.0000   0.6476
   0.250   0.2369   0.02410   0.01515  -0.0845   1.0000   1.0000
   0.500   0.2593   0.02484   0.01543  -0.0848   1.0000   1.0000
   0.750   0.2797   0.02562   0.01590  -0.0848   1.0000   1.0000
   1.000   0.2992   0.02645   0.01650  -0.0848   1.0000   1.0000
   1.250   0.3183   0.02733   0.01719  -0.0847   1.0000   1.0000
   1.500   0.3367   0.02826   0.01798  -0.0846   1.0000   1.0000
   1.750   0.3622   0.02938   0.01896  -0.0859   0.9963   1.0000
   2.000   0.4082   0.03092   0.02035  -0.0908   0.9837   1.0000
   2.250   0.4502   0.03227   0.02162  -0.0949   0.9704   1.0000
   2.500   0.4903   0.03354   0.02284  -0.0985   0.9568   1.0000
   2.750   0.5288   0.03472   0.02401  -0.1017   0.9429   1.0000
   3.000   0.5656   0.03584   0.02515  -0.1045   0.9286   1.0000
   3.250   0.6009   0.03693   0.02630  -0.1069   0.9142   1.0000
   3.500   0.6349   0.03799   0.02742  -0.1090   0.8997   1.0000
   3.750   0.6676   0.03903   0.02855  -0.1108   0.8850   1.0000
   4.000   0.6988   0.04007   0.02969  -0.1122   0.8697   1.0000
   4.250   0.7294   0.04110   0.03089  -0.1135   0.8541   1.0000
   4.500   0.7599   0.04211   0.03205  -0.1146   0.8379   1.0000
   4.750   0.7941   0.04294   0.03307  -0.1159   0.8202   1.0000
   5.000   0.8438   0.04293   0.03337  -0.1181   0.7983   1.0000
   5.250   0.8999   0.04190   0.03268  -0.1198   0.7723   1.0000
   5.500   0.9342   0.04170   0.03277  -0.1193   0.7482   1.0000
   5.750   1.0032   0.03947   0.03111  -0.1215   0.7285   1.0000
   6.000   1.0513   0.03745   0.02956  -0.1205   0.7019   1.0000
   6.250   1.1331   0.02841   0.02105  -0.1147   0.6348   1.0000
   6.500   1.1588   0.02609   0.01882  -0.1089   0.5634   1.0000
   6.750   1.1604   0.02593   0.01799  -0.1008   0.4175   1.0000
   7.000   1.1456   0.02953   0.01971  -0.0934   0.2554   1.0000
   7.250   1.1556   0.03307   0.02232  -0.0905   0.1862   1.0000
   7.500   1.1921   0.03629   0.02529  -0.0907   0.1505   1.0000
   7.750   1.2280   0.03934   0.02817  -0.0912   0.1302   1.0000
   8.000   1.2584   0.04234   0.03138  -0.0908   0.1181   1.0000
   8.250   1.2832   0.04566   0.03505  -0.0898   0.1101   1.0000
   8.500   1.3073   0.04931   0.03907  -0.0887   0.1057   1.0000
   8.750   1.3272   0.05347   0.04342  -0.0877   0.1012   1.0000
   9.000   1.3346   0.05716   0.04786  -0.0848   0.0988   1.0000
   9.250   1.3406   0.06149   0.05274  -0.0822   0.0980   1.0000
   9.500   1.3430   0.06620   0.05794  -0.0797   0.0986   1.0000
   9.750   1.3414   0.07110   0.06328  -0.0771   0.0997   1.0000
  10.000   1.3394   0.07628   0.06878  -0.0750   0.1008   1.0000
  10.250   1.3390   0.08184   0.07458  -0.0734   0.1018   1.0000
  10.500   1.2936   0.08528   0.07865  -0.0687   0.1050   1.0000
  10.750   1.2544   0.08985   0.08349  -0.0661   0.1069   1.0000
  11.000   1.2192   0.09557   0.08940  -0.0662   0.1086   1.0000
  11.250   1.1875   0.10245   0.09634  -0.0683   0.1106   1.0000
  11.500   1.1662   0.10987   0.10383  -0.0711   0.1130   1.0000
  11.750   1.1225   0.12158   0.11558  -0.0799   0.1181   1.0000
  12.000   1.1003   0.13389   0.12783  -0.0874   0.1273   1.0000
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