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GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 374 AIRFOIL (goe374-il)
Reynolds number: 500,000
Max Cl/Cd: 98.68 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe374-il-500000.txt
Download as CSV file: xf-goe374-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 374 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3421   0.08785   0.08573  -0.0157   1.0000   0.0113
  -7.250  -0.3431   0.08551   0.08343  -0.0156   1.0000   0.0117
  -7.000  -0.3404   0.08289   0.08085  -0.0169   1.0000   0.0125
  -6.750  -0.3348   0.08019   0.07817  -0.0189   1.0000   0.0126
  -6.500  -0.3274   0.07756   0.07555  -0.0219   1.0000   0.0128
  -6.250  -0.3193   0.07497   0.07296  -0.0251   1.0000   0.0129
  -6.000  -0.3127   0.07240   0.07039  -0.0265   0.9999   0.0129
  -5.750  -0.2754   0.06735   0.06526  -0.0345   0.9964   0.0130
  -5.500  -0.2575   0.06175   0.05967  -0.0371   0.9929   0.0133
  -5.250  -0.2301   0.05767   0.05555  -0.0414   0.9883   0.0135
  -5.000  -0.1965   0.05365   0.05147  -0.0469   0.9844   0.0139
  -4.750  -0.1631   0.04982   0.04754  -0.0519   0.9790   0.0145
  -4.500  -0.1271   0.04595   0.04357  -0.0568   0.9737   0.0153
  -4.250  -0.0816   0.04220   0.03963  -0.0622   0.9700   0.0169
  -4.000  -0.0394   0.03920   0.03636  -0.0652   0.9615   0.0173
  -3.750  -0.0018   0.03575   0.03266  -0.0679   0.9550   0.0174
  -2.250   0.1595   0.02245   0.01803  -0.0683   0.8657   0.0233
  -2.000   0.1807   0.01860   0.01389  -0.0675   0.8470   0.0242
  -1.750   0.2038   0.01728   0.01243  -0.0670   0.8255   0.0255
  -1.500   0.2287   0.01647   0.01140  -0.0661   0.8011   0.0288
  -1.250   0.2567   0.01699   0.01152  -0.0646   0.7731   0.0312
  -1.000   0.2789   0.01413   0.00838  -0.0638   0.7428   0.0335
  -0.750   0.3031   0.01346   0.00750  -0.0629   0.7065   0.0364
   0.750   0.1968   0.00728   0.00105  -0.0311   0.6601   0.0403
   1.000   0.4811   0.01017   0.00298  -0.0576   0.5380   0.0496
   1.250   0.5059   0.00989   0.00256  -0.0568   0.5102   0.0464
   1.500   0.5309   0.00979   0.00233  -0.0561   0.4857   0.0456
   1.750   0.5562   0.00973   0.00219  -0.0556   0.4674   0.0464
   2.000   0.5819   0.00972   0.00209  -0.0550   0.4526   0.0449
   2.250   0.6076   0.00975   0.00204  -0.0545   0.4385   0.0442
   2.500   0.6334   0.00979   0.00201  -0.0541   0.4258   0.0444
   2.750   0.6595   0.00985   0.00201  -0.0537   0.4145   0.0456
   3.000   0.6857   0.00991   0.00203  -0.0533   0.4030   0.0484
   3.250   0.7119   0.01000   0.00208  -0.0530   0.3920   0.0517
   3.500   0.7334   0.00928   0.00229  -0.0521   0.3828   0.5570
   3.750   0.7873   0.00851   0.00247  -0.0582   0.3696   1.0000
   4.000   0.8130   0.00864   0.00258  -0.0577   0.3597   1.0000
   4.250   0.8385   0.00880   0.00270  -0.0572   0.3499   1.0000
   4.500   0.8638   0.00898   0.00283  -0.0567   0.3397   1.0000
   4.750   0.8891   0.00915   0.00299  -0.0563   0.3287   1.0000
   5.000   0.9145   0.00932   0.00315  -0.0558   0.3172   1.0000
   5.250   0.9394   0.00953   0.00331  -0.0553   0.3015   1.0000
   5.500   0.9641   0.00977   0.00349  -0.0548   0.2833   1.0000
   5.750   0.9886   0.01004   0.00370  -0.0542   0.2635   1.0000
   6.000   1.0123   0.01038   0.00397  -0.0536   0.2400   1.0000
   6.250   1.0359   0.01075   0.00425  -0.0530   0.2173   1.0000
   6.500   1.0585   0.01124   0.00458  -0.0522   0.1855   1.0000
   6.750   1.0798   0.01189   0.00500  -0.0514   0.1478   1.0000
   7.000   1.1013   0.01251   0.00548  -0.0505   0.1218   1.0000
   7.250   1.1229   0.01312   0.00595  -0.0497   0.0964   1.0000
   7.500   1.1362   0.01473   0.00706  -0.0477   0.0228   1.0000
   7.750   1.1568   0.01547   0.00783  -0.0465   0.0169   1.0000
   8.000   1.1781   0.01613   0.00867  -0.0454   0.0147   1.0000
   8.250   1.1988   0.01680   0.00949  -0.0443   0.0140   1.0000
   8.500   1.2183   0.01760   0.01043  -0.0430   0.0133   1.0000
   8.750   1.2362   0.01852   0.01148  -0.0415   0.0125   1.0000
   9.000   1.2525   0.01954   0.01261  -0.0399   0.0116   1.0000
   9.250   1.2668   0.02069   0.01387  -0.0380   0.0110   1.0000
   9.500   1.2776   0.02205   0.01534  -0.0358   0.0104   1.0000
   9.750   1.2844   0.02366   0.01709  -0.0330   0.0100   1.0000
  10.000   1.2879   0.02544   0.01898  -0.0298   0.0097   1.0000
  10.250   1.2870   0.02732   0.02096  -0.0260   0.0096   1.0000
  10.500   1.2820   0.03013   0.02387  -0.0220   0.0093   1.0000
  10.750   1.2882   0.03238   0.02622  -0.0197   0.0093   1.0000
  11.000   1.2975   0.03450   0.02844  -0.0178   0.0093   1.0000
  11.250   1.3069   0.03654   0.03059  -0.0161   0.0093   1.0000
  11.500   1.3137   0.03805   0.03221  -0.0142   0.0094   1.0000
  11.750   1.3207   0.04071   0.03503  -0.0126   0.0094   1.0000
  12.000   1.3249   0.04351   0.03799  -0.0110   0.0094   1.0000
  12.250   1.3241   0.04772   0.04245  -0.0095   0.0093   1.0000
  12.500   1.3237   0.04914   0.04398  -0.0080   0.0094   1.0000
  12.750   1.3209   0.05130   0.04629  -0.0070   0.0095   1.0000
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