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GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 456 AIRFOIL (goe456-il)
Reynolds number: 50,000
Max Cl/Cd: 42.92 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe456-il-50000.txt
Download as CSV file: xf-goe456-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 456 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  -0.3219   0.10391   0.09776  -0.0279   1.0000   0.1610
  -7.250  -0.3415   0.10433   0.09835  -0.0259   1.0000   0.1633
  -7.000  -0.3622   0.10512   0.09932  -0.0256   1.0000   0.1643
  -6.750  -0.3429   0.09863   0.09282  -0.0218   1.0000   0.1704
  -6.500  -0.3519   0.09740   0.09170  -0.0205   1.0000   0.1751
  -6.250  -0.3693   0.09796   0.09240  -0.0222   1.0000   0.1780
  -6.000  -0.3619   0.09319   0.08769  -0.0181   1.0000   0.1823
  -5.750  -0.3651   0.09124   0.08581  -0.0172   1.0000   0.1886
  -5.000  -0.3683   0.08541   0.08010  -0.0209   1.0000   0.2065
  -4.750  -0.3656   0.08158   0.07634  -0.0161   1.0000   0.2115
  -4.500  -0.3600   0.07943   0.07420  -0.0199   1.0000   0.2212
  -4.250  -0.3559   0.07635   0.07118  -0.0172   1.0000   0.2285
  -4.000  -0.3479   0.07351   0.06835  -0.0187   1.0000   0.2379
  -3.750  -0.3368   0.07072   0.06554  -0.0208   1.0000   0.2502
  -3.250  -0.3138   0.06505   0.05986  -0.0223   1.0000   0.2789
  -3.000  -0.2989   0.06246   0.05724  -0.0240   1.0000   0.3045
  -2.750  -0.2871   0.05980   0.05459  -0.0236   1.0000   0.3320
  -2.500  -0.2771   0.05709   0.05190  -0.0221   1.0000   0.3609
  -2.250  -0.1318   0.04571   0.03876  -0.0584   1.0000   0.1492
  -2.000  -0.0853   0.04023   0.03242  -0.0639   1.0000   0.1220
  -1.750  -0.0562   0.03740   0.02915  -0.0653   1.0000   0.1180
  -1.500  -0.0258   0.03502   0.02619  -0.0667   1.0000   0.1177
  -1.250   0.0005   0.03355   0.02429  -0.0672   1.0000   0.1267
  -1.000   0.0273   0.03223   0.02247  -0.0675   1.0000   0.1345
  -0.750   0.0521   0.03121   0.02115  -0.0674   1.0000   0.1468
  -0.500   0.0757   0.03071   0.02053  -0.0672   1.0000   0.1815
  -0.250   0.1059   0.02970   0.01967  -0.0676   1.0000   0.3083
   0.000   0.1353   0.02943   0.01967  -0.0688   0.9967   0.4471
   0.250   0.1787   0.02934   0.01971  -0.0723   0.9889   0.5230
   0.500   0.2176   0.02853   0.01972  -0.0751   0.9801   1.0000
   0.750   0.2583   0.02969   0.02012  -0.0786   0.9709   1.0000
   1.000   0.2894   0.03067   0.02064  -0.0805   0.9617   1.0000
   1.250   0.3236   0.03177   0.02141  -0.0829   0.9528   1.0000
   1.500   0.3566   0.03284   0.02223  -0.0851   0.9441   1.0000
   1.750   0.3829   0.03381   0.02301  -0.0861   0.9348   1.0000
   2.000   0.4145   0.03492   0.02395  -0.0881   0.9263   1.0000
   2.250   0.4446   0.03598   0.02488  -0.0897   0.9171   1.0000
   2.500   0.4676   0.03700   0.02582  -0.0902   0.9078   1.0000
   2.750   0.4974   0.03812   0.02688  -0.0917   0.8984   1.0000
   3.000   0.5317   0.03925   0.02800  -0.0939   0.8886   1.0000
   3.250   0.5541   0.04027   0.02901  -0.0941   0.8773   1.0000
   3.500   0.5804   0.04132   0.03007  -0.0949   0.8652   1.0000
   3.750   0.6137   0.04224   0.03104  -0.0965   0.8506   1.0000
   4.000   0.6573   0.04285   0.03173  -0.0989   0.8327   1.0000
   4.250   0.6849   0.04345   0.03247  -0.0990   0.8132   1.0000
   4.500   0.7295   0.04365   0.03282  -0.1009   0.7946   1.0000
   4.750   0.7651   0.04399   0.03333  -0.1017   0.7770   1.0000
   5.000   0.7923   0.04448   0.03400  -0.1014   0.7585   1.0000
   5.250   0.8340   0.04437   0.03424  -0.1023   0.7408   1.0000
   5.500   0.8737   0.04410   0.03427  -0.1027   0.7220   1.0000
   5.750   0.9104   0.04371   0.03421  -0.1024   0.7013   1.0000
   6.000   0.9797   0.04121   0.03238  -0.1043   0.6839   1.0000
   6.250   1.0962   0.02842   0.02021  -0.0997   0.6132   1.0000
   6.500   1.1135   0.02653   0.01833  -0.0935   0.5529   1.0000
   6.750   1.1223   0.02615   0.01800  -0.0880   0.4906   1.0000
   7.000   1.1241   0.02655   0.01810  -0.0822   0.3933   1.0000
   7.250   1.1168   0.02848   0.01886  -0.0764   0.2619   1.0000
   7.500   1.1070   0.03121   0.02078  -0.0717   0.1563   1.0000
   7.750   1.1022   0.03390   0.02284  -0.0679   0.1046   1.0000
   8.000   1.1018   0.03635   0.02505  -0.0648   0.0899   1.0000
   8.250   1.1043   0.03861   0.02734  -0.0620   0.0820   1.0000
   8.500   1.1082   0.04085   0.02965  -0.0594   0.0780   1.0000
   8.750   1.1154   0.04313   0.03198  -0.0569   0.0752   1.0000
   9.000   1.1416   0.04483   0.03390  -0.0550   0.0725   1.0000
   9.250   1.2361   0.04805   0.03753  -0.0591   0.0696   1.0000
   9.500   1.2806   0.05218   0.04193  -0.0604   0.0666   1.0000
   9.750   1.3053   0.05621   0.04648  -0.0595   0.0668   1.0000
  10.000   1.3145   0.06028   0.05121  -0.0570   0.0689   1.0000
  10.250   1.3188   0.06472   0.05618  -0.0545   0.0711   1.0000
  10.500   1.3201   0.06936   0.06122  -0.0522   0.0731   1.0000
  10.750   1.3294   0.07519   0.06726  -0.0511   0.0752   1.0000
  11.000   1.3149   0.07827   0.07080  -0.0475   0.0768   1.0000
  11.250   1.2857   0.08126   0.07415  -0.0436   0.0775   1.0000
  11.500   1.2565   0.08512   0.07832  -0.0414   0.0782   1.0000
  11.750   1.2271   0.08983   0.08328  -0.0407   0.0787   1.0000
  12.000   1.1977   0.09528   0.08895  -0.0416   0.0791   1.0000
  12.250   1.1677   0.10163   0.09546  -0.0441   0.0794   1.0000
  12.500   1.1364   0.10922   0.10318  -0.0483   0.0797   1.0000
  12.750   1.1043   0.11838   0.11241  -0.0544   0.0802   1.0000
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