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ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR04 AIRFOIL (hor04-il)
Reynolds number: 500,000
Max Cl/Cd: 58.7 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor04-il-500000-n5.txt
Download as CSV file: xf-hor04-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6414   0.10421   0.10203   0.0310   1.0000   0.0071
  -8.000  -0.6374   0.10053   0.09836   0.0290   1.0000   0.0072
  -7.750  -0.6338   0.09685   0.09470   0.0270   1.0000   0.0074
  -7.500  -0.6291   0.09304   0.09091   0.0242   1.0000   0.0075
  -7.250  -0.6194   0.08873   0.08660   0.0199   1.0000   0.0078
  -5.500  -0.4572   0.05221   0.04952  -0.0225   1.0000   0.0107
  -4.750  -0.3769   0.03621   0.03291  -0.0326   1.0000   0.0099
  -4.500  -0.3463   0.03171   0.02812  -0.0351   1.0000   0.0093
  -4.250  -0.3136   0.02740   0.02345  -0.0370   1.0000   0.0088
  -4.000  -0.2801   0.02336   0.01900  -0.0384   1.0000   0.0085
  -3.750  -0.2463   0.01956   0.01474  -0.0395   1.0000   0.0087
  -3.500  -0.2137   0.01661   0.01137  -0.0401   1.0000   0.0094
  -3.250  -0.1830   0.01477   0.00921  -0.0405   1.0000   0.0099
  -3.000  -0.1535   0.01386   0.00812  -0.0408   1.0000   0.0105
  -2.750  -0.1238   0.01239   0.00645  -0.0412   1.0000   0.0112
  -2.500  -0.0945   0.01141   0.00536  -0.0415   1.0000   0.0111
  -2.250  -0.0653   0.01055   0.00442  -0.0417   1.0000   0.0110
  -2.000  -0.0361   0.00978   0.00358  -0.0421   1.0000   0.0110
  -1.750  -0.0067   0.00912   0.00284  -0.0424   1.0000   0.0113
  -1.500   0.0225   0.00864   0.00231  -0.0427   1.0000   0.0119
  -1.250   0.0514   0.00833   0.00199  -0.0429   1.0000   0.0138
  -1.000   0.0800   0.00814   0.00179  -0.0431   1.0000   0.0181
  -0.750   0.1086   0.00795   0.00164  -0.0432   1.0000   0.0257
  -0.500   0.1394   0.00787   0.00158  -0.0439   0.9883   0.0350
  -0.250   0.1732   0.00707   0.00159  -0.0458   0.9608   0.3094
   0.000   0.2007   0.00650   0.00171  -0.0459   0.9211   0.5510
   0.250   0.2232   0.00615   0.00181  -0.0445   0.8769   0.7191
   0.500   0.2413   0.00538   0.00153  -0.0415   0.8340   1.0000
   0.750   0.2663   0.00570   0.00153  -0.0406   0.7662   1.0000
   1.000   0.2919   0.00627   0.00154  -0.0400   0.6370   1.0000
   1.250   0.3193   0.00675   0.00162  -0.0401   0.5534   1.0000
   1.500   0.3472   0.00713   0.00168  -0.0402   0.4694   1.0000
   1.750   0.3750   0.00784   0.00184  -0.0406   0.3248   1.0000
   2.000   0.4030   0.00854   0.00205  -0.0411   0.2032   1.0000
   2.250   0.4311   0.00928   0.00230  -0.0416   0.0838   1.0000
   2.500   0.4593   0.00961   0.00251  -0.0418   0.0563   1.0000
   2.750   0.4875   0.00986   0.00272  -0.0419   0.0450   1.0000
   3.000   0.5157   0.01014   0.00299  -0.0420   0.0384   1.0000
   3.250   0.5438   0.01041   0.00329  -0.0421   0.0353   1.0000
   3.500   0.5719   0.01068   0.00360  -0.0422   0.0329   1.0000
   3.750   0.5999   0.01099   0.00392  -0.0423   0.0296   1.0000
   4.000   0.6277   0.01137   0.00430  -0.0424   0.0252   1.0000
   4.250   0.6556   0.01163   0.00465  -0.0425   0.0232   1.0000
   4.500   0.6834   0.01193   0.00500  -0.0425   0.0204   1.0000
   4.750   0.7109   0.01241   0.00549  -0.0426   0.0162   1.0000
   5.000   0.7385   0.01263   0.00574  -0.0426   0.0136   1.0000
   5.250   0.7660   0.01305   0.00618  -0.0427   0.0110   1.0000
   5.500   0.7931   0.01391   0.00714  -0.0426   0.0093   1.0000
   5.750   0.8200   0.01464   0.00804  -0.0426   0.0086   1.0000
   6.000   0.8467   0.01555   0.00909  -0.0424   0.0078   1.0000
   6.250   0.8731   0.01664   0.01036  -0.0423   0.0072   1.0000
   6.500   0.8991   0.01785   0.01177  -0.0421   0.0067   1.0000
   6.750   0.9251   0.01874   0.01280  -0.0420   0.0062   1.0000
   7.000   0.9491   0.02118   0.01562  -0.0417   0.0054   1.0000
   7.250   0.9728   0.02365   0.01850  -0.0413   0.0052   1.0000
   7.500   0.9949   0.02687   0.02226  -0.0409   0.0050   1.0000
   7.750   0.9996   0.04029   0.03693  -0.0393   0.0046   1.0000
   8.000   0.9944   0.05449   0.05182  -0.0392   0.0044   1.0000
   8.250   0.9904   0.06452   0.06221  -0.0410   0.0044   1.0000
   8.500   0.9843   0.07343   0.07133  -0.0444   0.0044   1.0000
   8.750   0.9757   0.08203   0.08005  -0.0498   0.0044   1.0000
   9.000   0.9630   0.09033   0.08839  -0.0584   0.0045   1.0000
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