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ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR04 AIRFOIL (hor04-il)
Reynolds number: 100,000
Max Cl/Cd: 45.24 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor04-il-100000.txt
Download as CSV file: xf-hor04-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6337   0.11780   0.11290   0.0289   1.0000   0.0490
  -8.500  -0.6324   0.11522   0.11037   0.0247   1.0000   0.0502
  -8.250  -0.6323   0.11278   0.10800   0.0196   1.0000   0.0507
  -8.000  -0.6260   0.10962   0.10486   0.0117   1.0000   0.0511
  -7.750  -0.6139   0.10559   0.10080   0.0025   1.0000   0.0513
  -7.500  -0.6134   0.09837   0.09367   0.0172   1.0000   0.0541
  -7.250  -0.6047   0.09436   0.08967   0.0157   1.0000   0.0563
  -7.000  -0.5944   0.09023   0.08555   0.0121   1.0000   0.0587
  -6.750  -0.5803   0.08578   0.08109   0.0058   1.0000   0.0617
  -6.500  -0.5471   0.08116   0.07617  -0.0129   1.0000   0.0647
  -6.250  -0.5399   0.07501   0.07016  -0.0113   1.0000   0.0662
  -6.000  -0.5299   0.07124   0.06643  -0.0092   1.0000   0.0695
  -5.750  -0.5071   0.06677   0.06180  -0.0143   1.0000   0.0751
  -5.500  -0.4778   0.06120   0.05598  -0.0224   1.0000   0.0803
  -5.250  -0.4607   0.05754   0.05234  -0.0225   1.0000   0.0859
  -5.000  -0.4052   0.03889   0.03400  -0.0253   1.0000   0.0992
  -4.750  -0.3822   0.03430   0.02923  -0.0288   1.0000   0.1106
  -4.500  -0.3594   0.03039   0.02519  -0.0311   1.0000   0.1255
  -4.250  -0.3365   0.02679   0.02145  -0.0331   1.0000   0.1513
  -3.000  -0.1818   0.02613   0.01839  -0.0453   1.0000   0.1567
  -2.500  -0.1047   0.02063   0.01135  -0.0444   1.0000   0.0706
  -2.250  -0.0739   0.01895   0.00933  -0.0441   1.0000   0.0684
  -2.000  -0.0449   0.01765   0.00791  -0.0440   1.0000   0.0749
  -1.750  -0.0160   0.01632   0.00648  -0.0436   1.0000   0.0769
  -1.500   0.0119   0.01491   0.00520  -0.0433   1.0000   0.0829
  -1.250   0.0400   0.01396   0.00433  -0.0433   1.0000   0.1022
  -1.000   0.0693   0.01291   0.00345  -0.0433   1.0000   0.1475
  -0.750   0.0830   0.00987   0.00279  -0.0394   1.0000   1.0000
  -0.500   0.1108   0.00990   0.00254  -0.0393   1.0000   1.0000
  -0.250   0.1384   0.00994   0.00241  -0.0393   1.0000   1.0000
   0.000   0.1657   0.00999   0.00235  -0.0392   1.0000   1.0000
   0.250   0.1928   0.01005   0.00235  -0.0392   1.0000   1.0000
   0.500   0.2197   0.01013   0.00240  -0.0391   1.0000   1.0000
   0.750   0.2464   0.01023   0.00251  -0.0390   1.0000   1.0000
   1.000   0.2728   0.01034   0.00266  -0.0389   1.0000   1.0000
   1.250   0.2989   0.01048   0.00286  -0.0388   1.0000   1.0000
   1.500   0.3247   0.01066   0.00312  -0.0387   1.0000   1.0000
   1.750   0.3503   0.01087   0.00345  -0.0387   1.0000   1.0000
   2.000   0.3756   0.01113   0.00390  -0.0387   1.0000   1.0000
   2.250   0.4006   0.01148   0.00442  -0.0388   1.0000   1.0000
   2.500   0.4622   0.01138   0.00463  -0.0457   0.9680   1.0000
   2.750   0.5103   0.01128   0.00466  -0.0476   0.8592   1.0000
   3.000   0.5230   0.01195   0.00475  -0.0412   0.6563   1.0000
   3.250   0.5370   0.01578   0.00568  -0.0385   0.1413   1.0000
   3.500   0.5636   0.01712   0.00689  -0.0381   0.1166   1.0000
   3.750   0.5899   0.01847   0.00814  -0.0377   0.1017   1.0000
   4.000   0.6166   0.02002   0.00965  -0.0372   0.0913   1.0000
   4.250   0.6439   0.02202   0.01159  -0.0368   0.0850   1.0000
   4.500   0.6725   0.02386   0.01381  -0.0362   0.0779   1.0000
   4.750   0.7000   0.02645   0.01649  -0.0360   0.0717   1.0000
   5.000   0.7287   0.02960   0.02018  -0.0355   0.0692   1.0000
   5.250   0.7572   0.03223   0.02351  -0.0348   0.0651   1.0000
   5.500   0.7838   0.03691   0.02866  -0.0344   0.0690   1.0000
   6.500   0.8849   0.06250   0.05725  -0.0366   0.1398   1.0000
   6.750   0.8987   0.06697   0.06159  -0.0357   0.1249   1.0000
   7.000   0.9074   0.07102   0.06602  -0.0375   0.1125   1.0000
   7.250   0.9090   0.07705   0.07239  -0.0420   0.1039   1.0000
   7.500   0.9239   0.08082   0.07609  -0.0392   0.0984   1.0000
   7.750   0.8149   0.07964   0.07545  -0.0380   0.1078   1.0000
   8.000   0.7966   0.08572   0.08154  -0.0420   0.1072   1.0000
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