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GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 439 AIRFOIL (goe439-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.26 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe439-il-1000000.txt
Download as CSV file: xf-goe439-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 439 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3072   0.10354   0.10194  -0.0274   1.0000   0.0083
  -9.000  -0.3038   0.10076   0.09917  -0.0279   1.0000   0.0086
  -8.750  -0.3013   0.09793   0.09637  -0.0282   1.0000   0.0090
  -8.000  -0.1989   0.07019   0.06878  -0.0423   0.9902   0.0104
  -7.750  -0.1865   0.06637   0.06497  -0.0452   0.9854   0.0106
  -7.500  -0.1743   0.06272   0.06131  -0.0482   0.9785   0.0109
  -7.250  -0.1582   0.05834   0.05693  -0.0530   0.9721   0.0113
  -7.000  -0.1403   0.05385   0.05242  -0.0586   0.9612   0.0120
  -6.750  -0.1222   0.04888   0.04741  -0.0654   0.9437   0.0127
  -6.500  -0.1075   0.04413   0.04257  -0.0723   0.9160   0.0138
  -6.250  -0.0977   0.04012   0.03844  -0.0757   0.8879   0.0139
  -6.000  -0.0864   0.03620   0.03441  -0.0788   0.8642   0.0139
  -5.750  -0.0731   0.03181   0.02988  -0.0822   0.8444   0.0139
  -5.500  -0.0718   0.01646   0.01304  -0.1061   0.8789   0.0098
  -5.250  -0.0527   0.01249   0.00826  -0.1053   0.8600   0.0104
  -4.750  -0.0028   0.01097   0.00629  -0.1043   0.8268   0.0114
  -4.500   0.0230   0.01043   0.00557  -0.1037   0.8118   0.0120
  -4.250   0.0490   0.00995   0.00491  -0.1032   0.7981   0.0127
  -4.000   0.0754   0.00970   0.00454  -0.1028   0.7853   0.0136
  -3.750   0.1010   0.00891   0.00355  -0.1023   0.7734   0.0150
  -3.500   0.1276   0.00861   0.00318  -0.1019   0.7620   0.0162
  -3.250   0.1545   0.00843   0.00291  -0.1016   0.7513   0.0177
  -3.000   0.1814   0.00829   0.00269  -0.1013   0.7409   0.0191
  -2.750   0.2079   0.00791   0.00224  -0.1009   0.7307   0.0225
  -2.500   0.2351   0.00786   0.00215  -0.1006   0.7206   0.0255
  -2.250   0.2618   0.00762   0.00183  -0.1003   0.7106   0.0297
  -1.750   0.3162   0.00753   0.00167  -0.0998   0.6892   0.0367
  -1.500   0.3430   0.00731   0.00139  -0.0995   0.6782   0.0434
  -1.250   0.3700   0.00727   0.00128  -0.0992   0.6663   0.0476
  -1.000   0.3969   0.00717   0.00115  -0.0989   0.6536   0.0561
  -0.750   0.4235   0.00707   0.00110  -0.0986   0.6397   0.0867
  -0.500   0.4504   0.00707   0.00109  -0.0984   0.6242   0.1082
  -0.250   0.4773   0.00711   0.00107  -0.0981   0.6075   0.1183
   0.000   0.5039   0.00714   0.00106  -0.0978   0.5897   0.1268
   0.250   0.5304   0.00721   0.00104  -0.0975   0.5724   0.1336
   0.500   0.5569   0.00726   0.00105  -0.0972   0.5558   0.1424
   0.750   0.5835   0.00729   0.00106  -0.0969   0.5406   0.1565
   1.000   0.6097   0.00722   0.00111  -0.0967   0.5263   0.2256
   1.250   0.6326   0.00659   0.00126  -0.0961   0.5131   0.5708
   1.500   0.6718   0.00580   0.00135  -0.0987   0.4966   1.0000
   1.750   0.6977   0.00594   0.00140  -0.0983   0.4819   1.0000
   2.000   0.7238   0.00608   0.00146  -0.0979   0.4694   1.0000
   2.250   0.7499   0.00621   0.00153  -0.0975   0.4579   1.0000
   2.500   0.7762   0.00632   0.00159  -0.0972   0.4470   1.0000
   2.750   0.8024   0.00646   0.00167  -0.0968   0.4354   1.0000
   3.000   0.8284   0.00660   0.00175  -0.0965   0.4230   1.0000
   3.250   0.8544   0.00675   0.00186  -0.0961   0.4118   1.0000
   3.500   0.8803   0.00691   0.00196  -0.0958   0.4006   1.0000
   3.750   0.9060   0.00709   0.00208  -0.0954   0.3856   1.0000
   4.000   0.9319   0.00725   0.00219  -0.0950   0.3734   1.0000
   4.250   0.9578   0.00741   0.00233  -0.0947   0.3616   1.0000
   4.750   1.0081   0.00786   0.00264  -0.0938   0.3276   1.0000
   5.000   1.0330   0.00811   0.00281  -0.0933   0.3087   1.0000
   5.250   1.0577   0.00837   0.00301  -0.0928   0.2904   1.0000
   5.500   1.0817   0.00869   0.00323  -0.0923   0.2671   1.0000
   5.750   1.1041   0.00917   0.00353  -0.0914   0.2327   1.0000
   6.000   1.1233   0.00995   0.00399  -0.0902   0.1757   1.0000
   6.250   1.1343   0.01154   0.00500  -0.0877   0.0706   1.0000
   6.500   1.1516   0.01255   0.00578  -0.0859   0.0228   1.0000
   6.750   1.1750   0.01289   0.00616  -0.0853   0.0200   1.0000
   7.000   1.1963   0.01345   0.00676  -0.0842   0.0160   1.0000
   7.250   1.2184   0.01390   0.00727  -0.0832   0.0146   1.0000
   7.500   1.2407   0.01430   0.00771  -0.0824   0.0132   1.0000
   7.750   1.2622   0.01476   0.00819  -0.0814   0.0119   1.0000
   8.000   1.2770   0.01582   0.00937  -0.0793   0.0103   1.0000
   8.250   1.2980   0.01625   0.00985  -0.0783   0.0100   1.0000
   8.500   1.3172   0.01681   0.01046  -0.0770   0.0094   1.0000
   8.750   1.3352   0.01743   0.01115  -0.0755   0.0089   1.0000
   9.000   1.3516   0.01812   0.01190  -0.0738   0.0084   1.0000
   9.250   1.3672   0.01880   0.01263  -0.0720   0.0080   1.0000
   9.500   1.3789   0.01962   0.01350  -0.0696   0.0074   1.0000
   9.750   1.3707   0.02128   0.01530  -0.0639   0.0070   1.0000
  10.000   1.3767   0.02227   0.01638  -0.0608   0.0067   1.0000
  10.250   1.3866   0.02308   0.01726  -0.0584   0.0066   1.0000
  10.500   1.3912   0.02427   0.01853  -0.0555   0.0064   1.0000
  10.750   1.3963   0.02551   0.01987  -0.0530   0.0062   1.0000
  11.000   1.3985   0.02706   0.02151  -0.0504   0.0060   1.0000
  11.250   1.4009   0.02872   0.02326  -0.0481   0.0059   1.0000
  11.500   1.4068   0.03018   0.02480  -0.0465   0.0056   1.0000
  11.750   1.4091   0.03207   0.02678  -0.0447   0.0056   1.0000
  12.000   1.4096   0.03428   0.02910  -0.0431   0.0055   1.0000
  12.250   1.4139   0.03618   0.03108  -0.0420   0.0053   1.0000
  12.500   1.4183   0.03813   0.03310  -0.0411   0.0051   1.0000
  12.750   1.4185   0.04067   0.03574  -0.0401   0.0051   1.0000
  13.000   1.4205   0.04305   0.03821  -0.0395   0.0050   1.0000
  13.250   1.4203   0.04578   0.04102  -0.0390   0.0048   1.0000
  13.500   1.4169   0.04899   0.04433  -0.0385   0.0047   1.0000
  13.750   1.4107   0.05275   0.04824  -0.0377   0.0046   1.0000
  14.000   1.3962   0.05818   0.05394  -0.0365   0.0044   1.0000
  14.250   1.3953   0.06125   0.05714  -0.0372   0.0043   1.0000
  14.500   1.3923   0.06488   0.06091  -0.0379   0.0043   1.0000
  14.750   1.3871   0.06900   0.06518  -0.0387   0.0042   1.0000
  15.000   1.3805   0.07354   0.06989  -0.0400   0.0041   1.0000
  15.250   1.3747   0.07809   0.07458  -0.0415   0.0040   1.0000
  15.500   1.3626   0.08390   0.08056  -0.0434   0.0040   1.0000
  15.750   1.3508   0.08987   0.08671  -0.0457   0.0040   1.0000
  16.000   1.3411   0.09568   0.09266  -0.0483   0.0039   1.0000
  16.250   1.3202   0.10387   0.10107  -0.0519   0.0039   1.0000
  16.500   1.3086   0.11047   0.10781  -0.0553   0.0039   1.0000
  16.750   1.2908   0.11868   0.11620  -0.0597   0.0039   1.0000
  17.000   1.2710   0.12765   0.12533  -0.0647   0.0039   1.0000
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