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GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 509 AIRFOIL (goe509-il)
Reynolds number: 50,000
Max Cl/Cd: 19.8 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe509-il-50000.txt
Download as CSV file: xf-goe509-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 509 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  -0.3024   0.11119   0.10473  -0.0278   1.0000   0.1895
  -8.500  -0.3269   0.11160   0.10531  -0.0272   1.0000   0.1925
  -8.250  -0.3074   0.10632   0.10004  -0.0251   1.0000   0.2008
  -8.000  -0.3227   0.10552   0.09938  -0.0236   1.0000   0.2064
  -7.750  -0.3529   0.10598   0.10003  -0.0215   1.0000   0.2082
  -7.500  -0.3314   0.10089   0.09495  -0.0194   1.0000   0.2185
  -7.250  -0.3577   0.10076   0.09499  -0.0164   1.0000   0.2223
  -7.000  -0.3892   0.10100   0.09540  -0.0134   1.0000   0.2237
  -6.750  -0.3780   0.09683   0.09127  -0.0104   1.0000   0.2320
  -6.500  -0.3967   0.09596   0.09050  -0.0080   1.0000   0.2372
  -6.250  -0.4302   0.09655   0.09120  -0.0072   1.0000   0.2404
  -6.000  -0.4152   0.09176   0.08647  -0.0032   1.0000   0.2494
  -5.750  -0.4404   0.09175   0.08650  -0.0030   1.0000   0.2564
  -5.250  -0.4540   0.08785   0.08264  -0.0007   1.0000   0.2732
  -5.000  -0.4440   0.08312   0.07804   0.0039   1.0000   0.2815
  -4.750  -0.4505   0.08095   0.07587   0.0045   1.0000   0.2923
  -4.500  -0.4543   0.07917   0.07408   0.0049   1.0000   0.3061
  -4.250  -0.4541   0.07669   0.07160   0.0065   1.0000   0.3216
  -4.000  -0.4527   0.07378   0.06873   0.0088   1.0000   0.3379
  -3.750  -0.4508   0.07074   0.06575   0.0117   1.0000   0.3556
  -3.500  -0.4491   0.06806   0.06309   0.0144   1.0000   0.3771
  -3.250  -0.4493   0.06540   0.06046   0.0169   1.0000   0.4036
  -3.000  -0.4501   0.06285   0.05795   0.0200   1.0000   0.4341
  -2.750  -0.4520   0.06004   0.05523   0.0243   1.0000   0.4679
  -2.500  -0.4287   0.05645   0.05167   0.0245   0.9884   0.5188
  -2.250  -0.2475   0.04866   0.04075  -0.0196   0.9707   0.1780
  -2.000  -0.2048   0.04601   0.03770  -0.0230   0.9550   0.1754
  -1.750  -0.1621   0.04356   0.03476  -0.0260   0.9393   0.1718
  -1.500  -0.1191   0.04167   0.03227  -0.0286   0.9233   0.1745
  -1.250  -0.0741   0.04002   0.03006  -0.0315   0.9066   0.1791
  -1.000  -0.0279   0.03903   0.02884  -0.0347   0.8898   0.1907
  -0.750   0.0228   0.03808   0.02766  -0.0385   0.8736   0.2060
  -0.500   0.0818   0.03749   0.02694  -0.0437   0.8577   0.2363
  -0.250   0.2621   0.03271   0.02439  -0.0714   0.8505   1.0000
   0.000   0.3054   0.03300   0.02418  -0.0739   0.8330   1.0000
   0.250   0.3466   0.03325   0.02406  -0.0761   0.8166   1.0000
   0.500   0.3844   0.03355   0.02406  -0.0778   0.8014   1.0000
   0.750   0.4224   0.03381   0.02409  -0.0794   0.7879   1.0000
   1.000   0.4772   0.03352   0.02356  -0.0833   0.7779   1.0000
   1.250   0.4977   0.03421   0.02410  -0.0822   0.7634   1.0000
   1.500   0.5137   0.03509   0.02486  -0.0806   0.7498   1.0000
   1.750   0.5354   0.03584   0.02548  -0.0798   0.7382   1.0000
   2.000   0.5812   0.03571   0.02523  -0.0823   0.7297   1.0000
   2.250   0.5794   0.03734   0.02679  -0.0784   0.7167   1.0000
   2.500   0.5881   0.03865   0.02802  -0.0760   0.7062   1.0000
   2.750   0.6270   0.03878   0.02808  -0.0774   0.6981   1.0000
   3.000   0.6104   0.04115   0.03040  -0.0720   0.6860   1.0000
   3.250   0.6764   0.04009   0.02929  -0.0764   0.6802   1.0000
   3.500   0.6428   0.04333   0.03249  -0.0693   0.6676   1.0000
   3.750   0.6350   0.04568   0.03481  -0.0657   0.6573   1.0000
   4.000   0.6949   0.04447   0.03358  -0.0683   0.6493   1.0000
   4.250   0.6734   0.04741   0.03648  -0.0633   0.6366   1.0000
   4.500   0.6849   0.04853   0.03758  -0.0612   0.6241   1.0000
   4.750   0.7379   0.04703   0.03610  -0.0621   0.6130   1.0000
   5.000   0.8050   0.04479   0.03390  -0.0648   0.6018   1.0000
   5.250   0.7731   0.04838   0.03745  -0.0586   0.5889   1.0000
   5.500   0.7684   0.05073   0.03981  -0.0555   0.5768   1.0000
   5.750   0.8837   0.04534   0.03455  -0.0618   0.5693   1.0000
   6.000   0.8416   0.04974   0.03893  -0.0549   0.5559   1.0000
   6.250   0.8180   0.05355   0.04274  -0.0507   0.5424   1.0000
   6.500   0.8186   0.05582   0.04503  -0.0484   0.5294   1.0000
   6.750   0.9548   0.04823   0.03765  -0.0546   0.5225   1.0000
   7.000   0.9006   0.05377   0.04317  -0.0473   0.5087   1.0000
   7.250   0.8615   0.05966   0.04904  -0.0436   0.4942   1.0000
   7.500   0.8315   0.06552   0.05489  -0.0416   0.4805   1.0000
   7.750   0.8952   0.06219   0.05168  -0.0408   0.4737   1.0000
   8.000   0.8580   0.06915   0.05862  -0.0393   0.4608   1.0000
   8.250   0.8024   0.07810   0.06751  -0.0386   0.4501   1.0000
   8.500   0.8716   0.07447   0.06405  -0.0372   0.4431   1.0000
   8.750   0.7893   0.08688   0.07633  -0.0382   0.4392   1.0000
   9.000   0.7715   0.09276   0.08223  -0.0389   0.4391   1.0000
   9.250   0.7675   0.09763   0.08714  -0.0396   0.4411   1.0000
   9.500   0.7747   0.10175   0.09132  -0.0403   0.4429   1.0000
   9.750   0.6562   0.11862   0.10821  -0.0486   0.5548   1.0000
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