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GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 415 AIRFOIL (goe415-il)
Reynolds number: 100,000
Max Cl/Cd: 53.57 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe415-il-100000-n5.txt
Download as CSV file: xf-goe415-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 415 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3896   0.10604   0.10144  -0.0104   1.0000   0.0329
  -8.250  -0.3860   0.10305   0.09851  -0.0134   1.0000   0.0331
  -8.000  -0.3823   0.09996   0.09549  -0.0163   1.0000   0.0333
  -7.750  -0.3785   0.09677   0.09236  -0.0193   1.0000   0.0334
  -7.500  -0.3709   0.09312   0.08876  -0.0234   1.0000   0.0335
  -7.250  -0.3614   0.08918   0.08486  -0.0280   1.0000   0.0336
  -7.000  -0.3505   0.08506   0.08074  -0.0325   1.0000   0.0337
  -6.750  -0.3471   0.08030   0.07609  -0.0305   1.0000   0.0343
  -6.500  -0.3407   0.07679   0.07259  -0.0294   1.0000   0.0350
  -6.250  -0.3321   0.07337   0.06920  -0.0304   1.0000   0.0358
  -6.000  -0.3229   0.06992   0.06577  -0.0321   1.0000   0.0365
  -5.750  -0.3130   0.06641   0.06227  -0.0341   1.0000   0.0373
  -5.500  -0.3020   0.06282   0.05868  -0.0361   1.0000   0.0381
  -5.250  -0.2898   0.05919   0.05500  -0.0381   1.0000   0.0391
  -5.000  -0.2755   0.05550   0.05122  -0.0401   1.0000   0.0408
  -4.750  -0.2520   0.05094   0.04620  -0.0451   1.0000   0.0455
  -4.500  -0.2300   0.04734   0.04277  -0.0467   0.9945   0.0497
  -4.250  -0.1898   0.04277   0.03787  -0.0530   0.9859   0.0618
  -4.000  -0.1430   0.03619   0.03069  -0.0569   0.9781   0.0283
  -3.000   0.0166   0.02326   0.01543  -0.0664   0.9355   0.0246
  -2.750   0.0527   0.02152   0.01342  -0.0678   0.9209   0.0274
  -2.500   0.0880   0.01986   0.01140  -0.0684   0.9045   0.0284
  -2.250   0.1213   0.01848   0.00976  -0.0686   0.8860   0.0301
  -2.000   0.1510   0.01755   0.00862  -0.0682   0.8634   0.0343
  -1.750   0.1781   0.01637   0.00743  -0.0676   0.8377   0.0377
  -1.500   0.2052   0.01571   0.00657  -0.0668   0.8073   0.0438
  -1.250   0.2325   0.01499   0.00563  -0.0661   0.7750   0.0524
  -0.750   0.2849   0.01295   0.00459  -0.0648   0.7137   0.4481
  -0.500   0.3200   0.01160   0.00422  -0.0650   0.6839   1.0000
  -0.250   0.3466   0.01179   0.00401  -0.0644   0.6568   1.0000
   0.250   0.3995   0.01220   0.00376  -0.0634   0.6097   1.0000
   0.500   0.4259   0.01241   0.00370  -0.0629   0.5894   1.0000
   0.750   0.4522   0.01264   0.00367  -0.0625   0.5714   1.0000
   1.000   0.4786   0.01287   0.00367  -0.0621   0.5549   1.0000
   1.250   0.5051   0.01311   0.00371  -0.0617   0.5392   1.0000
   1.500   0.5315   0.01335   0.00379  -0.0614   0.5244   1.0000
   1.750   0.5579   0.01360   0.00389  -0.0610   0.5103   1.0000
   2.250   0.6107   0.01411   0.00418  -0.0604   0.4834   1.0000
   2.500   0.6372   0.01436   0.00436  -0.0601   0.4706   1.0000
   2.750   0.6636   0.01462   0.00455  -0.0599   0.4579   1.0000
   3.000   0.6898   0.01488   0.00476  -0.0596   0.4454   1.0000
   3.250   0.7160   0.01515   0.00500  -0.0593   0.4336   1.0000
   3.500   0.7421   0.01544   0.00524  -0.0590   0.4226   1.0000
   3.750   0.7683   0.01573   0.00552  -0.0587   0.4119   1.0000
   4.000   0.7945   0.01604   0.00586  -0.0584   0.4013   1.0000
   4.250   0.8204   0.01636   0.00618  -0.0581   0.3913   1.0000
   4.500   0.8460   0.01669   0.00649  -0.0578   0.3811   1.0000
   4.750   0.8717   0.01701   0.00689  -0.0574   0.3695   1.0000
   5.000   0.8972   0.01735   0.00728  -0.0571   0.3586   1.0000
   5.250   0.9224   0.01771   0.00766  -0.0567   0.3475   1.0000
   5.500   0.9474   0.01808   0.00806  -0.0563   0.3369   1.0000
   5.750   0.9726   0.01845   0.00858  -0.0560   0.3267   1.0000
   6.000   0.9978   0.01886   0.00912  -0.0556   0.3183   1.0000
   6.250   1.0227   0.01930   0.00964  -0.0552   0.3104   1.0000
   6.500   1.0466   0.01966   0.01012  -0.0546   0.2960   1.0000
   6.750   1.0692   0.01996   0.01054  -0.0540   0.2703   1.0000
   7.000   1.0907   0.02039   0.01091  -0.0533   0.2342   1.0000
   7.250   1.1120   0.02105   0.01148  -0.0526   0.1921   1.0000
   7.750   1.1356   0.02532   0.01458  -0.0498   0.0280   1.0000
   8.000   1.1515   0.02687   0.01627  -0.0484   0.0218   1.0000
   8.250   1.1676   0.02829   0.01796  -0.0470   0.0196   1.0000
   8.500   1.1802   0.03005   0.01999  -0.0454   0.0175   1.0000
   8.750   1.1895   0.03202   0.02233  -0.0436   0.0160   1.0000
   9.000   1.1993   0.03373   0.02433  -0.0419   0.0153   1.0000
   9.250   1.2051   0.03566   0.02653  -0.0399   0.0149   1.0000
   9.500   1.2061   0.03771   0.02881  -0.0377   0.0146   1.0000
   9.750   1.2035   0.04000   0.03130  -0.0355   0.0144   1.0000
  10.000   1.1992   0.04265   0.03415  -0.0340   0.0142   1.0000
  10.250   1.1942   0.04567   0.03736  -0.0333   0.0140   1.0000
  10.500   1.1896   0.04900   0.04085  -0.0332   0.0137   1.0000
  10.750   1.1855   0.05255   0.04455  -0.0336   0.0134   1.0000
  11.000   1.1825   0.05612   0.04826  -0.0341   0.0130   1.0000
  11.250   1.1803   0.05964   0.05190  -0.0344   0.0125   1.0000
  11.500   1.1791   0.06303   0.05539  -0.0346   0.0121   1.0000
  11.750   1.1791   0.06627   0.05874  -0.0346   0.0116   1.0000
  12.000   1.1808   0.06926   0.06183  -0.0341   0.0114   1.0000
  12.250   1.1839   0.07215   0.06484  -0.0335   0.0112   1.0000
  12.500   1.1862   0.07528   0.06810  -0.0330   0.0111   1.0000
  12.750   1.1869   0.07876   0.07174  -0.0330   0.0110   1.0000
  13.000   1.1855   0.08266   0.07582  -0.0334   0.0110   1.0000
  13.250   1.1820   0.08697   0.08032  -0.0344   0.0110   1.0000
  13.500   1.1762   0.09170   0.08524  -0.0359   0.0110   1.0000
  13.750   1.1689   0.09677   0.09052  -0.0378   0.0110   1.0000
  14.000   1.1603   0.10221   0.09615  -0.0401   0.0110   1.0000
  14.250   1.1503   0.10809   0.10222  -0.0430   0.0111   1.0000
  14.500   1.1393   0.11443   0.10876  -0.0464   0.0112   1.0000
  14.750   1.1278   0.12118   0.11570  -0.0502   0.0112   1.0000
  15.000   1.1158   0.12836   0.12307  -0.0545   0.0113   1.0000
  15.250   1.1037   0.13595   0.13083  -0.0592   0.0114   1.0000
  15.500   1.0914   0.14401   0.13905  -0.0642   0.0116   1.0000
  15.750   1.0790   0.15260   0.14778  -0.0697   0.0117   1.0000
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