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ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR04 AIRFOIL (hor04-il)
Reynolds number: 200,000
Max Cl/Cd: 54.8 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor04-il-200000.txt
Download as CSV file: xf-hor04-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA HOR04 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.5511   0.08319   0.07965  -0.0068   1.0000   0.0254
  -6.500  -0.5537   0.07537   0.07193  -0.0063   1.0000   0.0266
  -6.250  -0.5459   0.07213   0.06870  -0.0048   1.0000   0.0284
  -6.000  -0.5272   0.06780   0.06433  -0.0087   1.0000   0.0304
  -5.750  -0.5035   0.06289   0.05931  -0.0141   1.0000   0.0321
  -5.500  -0.4758   0.05790   0.05414  -0.0197   1.0000   0.0341
  -5.250  -0.4323   0.05404   0.04984  -0.0267   1.0000   0.0373
  -5.000  -0.3999   0.05111   0.04650  -0.0298   1.0000   0.0378
  -4.750  -0.3798   0.04314   0.03849  -0.0333   1.0000   0.0393
  -4.500  -0.3566   0.03957   0.03489  -0.0348   1.0000   0.0413
  -4.250  -0.3281   0.03644   0.03158  -0.0367   1.0000   0.0447
  -4.000  -0.2880   0.03662   0.03098  -0.0376   1.0000   0.0512
  -3.750  -0.2632   0.02993   0.02436  -0.0405   1.0000   0.0549
  -2.250  -0.0701   0.01603   0.00835  -0.0433   1.0000   0.0422
  -2.000  -0.0399   0.01482   0.00689  -0.0429   1.0000   0.0392
  -1.750  -0.0109   0.01335   0.00536  -0.0429   1.0000   0.0404
  -1.500   0.0177   0.01246   0.00452  -0.0430   1.0000   0.0475
  -1.250   0.0468   0.01145   0.00353  -0.0432   1.0000   0.0547
  -1.000   0.0759   0.01074   0.00287  -0.0435   1.0000   0.0697
  -0.750   0.1038   0.00847   0.00241  -0.0445   1.0000   0.5779
  -0.500   0.1182   0.00715   0.00199  -0.0405   1.0000   1.0000
  -0.250   0.1461   0.00718   0.00189  -0.0405   1.0000   1.0000
   0.000   0.1738   0.00723   0.00186  -0.0405   1.0000   1.0000
   0.250   0.2014   0.00729   0.00187  -0.0406   1.0000   1.0000
   0.500   0.2288   0.00736   0.00192  -0.0405   1.0000   1.0000
   0.750   0.2561   0.00744   0.00202  -0.0405   1.0000   1.0000
   1.000   0.2831   0.00754   0.00215  -0.0405   1.0000   1.0000
   1.250   0.3100   0.00767   0.00233  -0.0405   1.0000   1.0000
   1.500   0.3367   0.00784   0.00257  -0.0406   1.0000   1.0000
   1.750   0.3786   0.00787   0.00272  -0.0438   0.9861   1.0000
   2.000   0.4264   0.00788   0.00273  -0.0470   0.9033   1.0000
   2.250   0.4472   0.00816   0.00285  -0.0443   0.8210   1.0000
   2.500   0.4667   0.00867   0.00294  -0.0414   0.7064   1.0000
   2.750   0.4884   0.00963   0.00311  -0.0396   0.5314   1.0000
   3.000   0.5117   0.01261   0.00399  -0.0402   0.0982   1.0000
   3.250   0.5397   0.01344   0.00479  -0.0402   0.0793   1.0000
   3.500   0.5670   0.01440   0.00572  -0.0403   0.0687   1.0000
   3.750   0.5944   0.01527   0.00663  -0.0401   0.0626   1.0000
   4.000   0.6207   0.01711   0.00839  -0.0399   0.0571   1.0000
   4.250   0.6487   0.01776   0.00921  -0.0396   0.0510   1.0000
   4.500   0.6754   0.01973   0.01124  -0.0394   0.0452   1.0000
   4.750   0.7036   0.02105   0.01289  -0.0390   0.0396   1.0000
   5.000   0.7316   0.02324   0.01538  -0.0385   0.0365   1.0000
   5.250   0.7587   0.02578   0.01821  -0.0382   0.0345   1.0000
   5.500   0.7933   0.03546   0.02947  -0.0355   0.0635   1.0000
   5.750   0.8168   0.03889   0.03312  -0.0354   0.0603   1.0000
   6.000   0.8317   0.04765   0.04187  -0.0366   0.0573   1.0000
   6.250   0.8582   0.04735   0.04252  -0.0353   0.0503   1.0000
   6.500   0.8761   0.05115   0.04657  -0.0354   0.0477   1.0000
   6.750   0.8918   0.05530   0.05077  -0.0355   0.0460   1.0000
   7.000   0.8958   0.06531   0.06081  -0.0369   0.0444   1.0000
   7.250   0.9064   0.06923   0.06516  -0.0372   0.0441   1.0000
   7.500   0.9160   0.07381   0.07036  -0.0404   0.0413   1.0000
   7.750   0.9190   0.08005   0.07679  -0.0439   0.0397   1.0000
   8.000   0.9188   0.08635   0.08320  -0.0481   0.0387   1.0000
   8.250   0.9158   0.09296   0.08986  -0.0538   0.0381   1.0000
   8.500   0.9082   0.09913   0.09601  -0.0596   0.0380   1.0000
   8.750   0.9040   0.10465   0.10150  -0.0635   0.0373   1.0000
   9.000   0.9019   0.10962   0.10645  -0.0662   0.0363   1.0000
   9.250   0.9038   0.11322   0.11005  -0.0665   0.0345   1.0000
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