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GOE 515 AIRFOIL (goe515-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 515 AIRFOIL (goe515-il)
Reynolds number: 50,000
Max Cl/Cd: 37.57 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe515-il-50000.txt
Download as CSV file: xf-goe515-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 515 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  -0.4206   0.10523   0.09799  -0.0217   1.0000   0.2283
  -8.500  -0.4059   0.10079   0.09355  -0.0205   1.0000   0.2392
  -8.250  -0.4328   0.10088   0.09384  -0.0216   1.0000   0.2444
  -8.000  -0.4120   0.09594   0.08886  -0.0200   1.0000   0.2575
  -7.750  -0.4057   0.09236   0.08533  -0.0190   1.0000   0.2658
  -7.500  -0.4300   0.09187   0.08504  -0.0182   1.0000   0.2741
  -7.250  -0.4144   0.08766   0.08082  -0.0166   1.0000   0.2862
  -7.000  -0.4148   0.08490   0.07812  -0.0147   1.0000   0.2980
  -6.750  -0.4202   0.08255   0.07587  -0.0126   1.0000   0.3114
  -6.500  -0.4233   0.08010   0.07353  -0.0106   1.0000   0.3265
  -6.250  -0.4259   0.07772   0.07123  -0.0081   1.0000   0.3435
  -6.000  -0.4310   0.07550   0.06910  -0.0055   1.0000   0.3608
  -5.750  -0.4449   0.07394   0.06765  -0.0029   1.0000   0.3796
  -5.500  -0.4418   0.07102   0.06479   0.0007   1.0000   0.3994
  -5.250  -0.4529   0.06955   0.06340   0.0045   1.0000   0.4260
  -5.000  -0.4512   0.06710   0.06102   0.0094   1.0000   0.4559
  -4.500  -0.4181   0.04970   0.04223  -0.0266   1.0000   0.2158
  -4.250  -0.4004   0.04513   0.03721  -0.0278   1.0000   0.2013
  -4.000  -0.3821   0.04161   0.03330  -0.0279   1.0000   0.1949
  -3.750  -0.3631   0.03841   0.02967  -0.0277   1.0000   0.1928
  -3.500  -0.3429   0.03585   0.02647  -0.0274   1.0000   0.1983
  -3.250  -0.3244   0.03397   0.02452  -0.0264   1.0000   0.2066
  -3.000  -0.3018   0.03186   0.02174  -0.0259   1.0000   0.2138
  -2.750  -0.2815   0.03048   0.02020  -0.0249   1.0000   0.2280
  -2.500  -0.2605   0.02918   0.01870  -0.0240   1.0000   0.2422
  -2.250  -0.2391   0.02814   0.01740  -0.0232   1.0000   0.2598
  -2.000  -0.2177   0.02714   0.01627  -0.0224   1.0000   0.2760
  -1.750  -0.1958   0.02630   0.01535  -0.0217   1.0000   0.2931
  -1.500  -0.1740   0.02558   0.01454  -0.0210   1.0000   0.3089
  -1.250  -0.1517   0.02500   0.01390  -0.0203   1.0000   0.3270
  -1.000  -0.1253   0.02452   0.01328  -0.0203   1.0000   0.3454
  -0.750  -0.0998   0.02408   0.01288  -0.0203   1.0000   0.3718
  -0.500  -0.0747   0.02364   0.01258  -0.0203   1.0000   0.4053
  -0.250  -0.0497   0.02293   0.01232  -0.0201   1.0000   0.4728
   0.000   0.0006   0.02127   0.01175  -0.0241   1.0000   1.0000
   0.250   0.0193   0.02172   0.01187  -0.0232   1.0000   1.0000
   0.500   0.0375   0.02221   0.01212  -0.0224   1.0000   1.0000
   0.750   0.0553   0.02273   0.01245  -0.0217   1.0000   1.0000
   1.000   0.0728   0.02329   0.01286  -0.0210   1.0000   1.0000
   1.250   0.0902   0.02390   0.01334  -0.0203   1.0000   1.0000
   1.500   0.1072   0.02455   0.01390  -0.0197   1.0000   1.0000
   1.750   0.1240   0.02526   0.01452  -0.0192   1.0000   1.0000
   2.000   0.1699   0.02662   0.01582  -0.0244   0.9868   1.0000
   2.250   0.2245   0.02814   0.01729  -0.0309   0.9694   1.0000
   2.500   0.2685   0.02924   0.01841  -0.0353   0.9507   1.0000
   2.750   0.3131   0.03033   0.01953  -0.0395   0.9319   1.0000
   3.000   0.3595   0.03138   0.02066  -0.0438   0.9134   1.0000
   3.250   0.4030   0.03231   0.02166  -0.0474   0.8944   1.0000
   3.500   0.4383   0.03311   0.02256  -0.0494   0.8737   1.0000
   3.750   0.4817   0.03387   0.02347  -0.0525   0.8543   1.0000
   4.000   0.5237   0.03454   0.02430  -0.0551   0.8348   1.0000
   4.250   0.5547   0.03523   0.02513  -0.0559   0.8132   1.0000
   4.500   0.6014   0.03555   0.02570  -0.0585   0.7935   1.0000
   4.750   0.6444   0.03532   0.02569  -0.0595   0.7672   1.0000
   5.000   0.7150   0.03307   0.02384  -0.0618   0.7371   1.0000
   5.250   0.7645   0.03154   0.02259  -0.0618   0.7113   1.0000
   5.500   0.8167   0.02969   0.02109  -0.0616   0.6862   1.0000
   5.750   0.8546   0.02835   0.02000  -0.0598   0.6556   1.0000
   6.000   0.8911   0.02682   0.01866  -0.0572   0.6163   1.0000
   6.250   0.9182   0.02547   0.01733  -0.0530   0.5606   1.0000
   6.500   0.9354   0.02490   0.01646  -0.0480   0.4875   1.0000
   6.750   0.9464   0.02563   0.01654  -0.0432   0.4028   1.0000
   7.000   0.9549   0.02721   0.01754  -0.0391   0.3275   1.0000
   7.250   0.9641   0.02897   0.01885  -0.0356   0.2665   1.0000
   7.500   0.9768   0.03091   0.02035  -0.0328   0.2177   1.0000
   7.750   0.9962   0.03330   0.02249  -0.0311   0.1803   1.0000
   8.000   1.0211   0.03619   0.02521  -0.0303   0.1539   1.0000
   8.250   1.0434   0.03907   0.02822  -0.0292   0.1369   1.0000
   8.500   1.0647   0.04221   0.03153  -0.0280   0.1261   1.0000
   8.750   1.0844   0.04510   0.03452  -0.0268   0.1168   1.0000
   9.000   1.0970   0.04880   0.03872  -0.0247   0.1134   1.0000
   9.250   1.1024   0.05232   0.04283  -0.0219   0.1110   1.0000
   9.500   1.1048   0.05588   0.04685  -0.0191   0.1084   1.0000
   9.750   1.1066   0.05940   0.05070  -0.0167   0.1059   1.0000
  10.000   1.1143   0.06313   0.05457  -0.0151   0.1033   1.0000
  10.250   1.0965   0.06729   0.05923  -0.0116   0.1044   1.0000
  10.500   1.0705   0.07173   0.06407  -0.0084   0.1063   1.0000
  10.750   1.0402   0.07600   0.06858  -0.0054   0.1081   1.0000
  11.000   1.0098   0.08093   0.07368  -0.0043   0.1103   1.0000
  11.250   0.9835   0.08658   0.07943  -0.0049   0.1122   1.0000
  11.500   0.9621   0.09280   0.08569  -0.0067   0.1137   1.0000
  11.750   0.9541   0.09891   0.09183  -0.0081   0.1150   1.0000
  12.000   0.8403   0.12600   0.11871  -0.0323   0.1507   1.0000
  12.250   0.7938   0.14966   0.14223  -0.0520   0.2866   1.0000
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