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ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR04 AIRFOIL (hor04-il)
Reynolds number: 1,000,000
Max Cl/Cd: 68.44 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor04-il-1000000.txt
Download as CSV file: xf-hor04-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6526   0.10659   0.10503   0.0326   1.0000   0.0059
  -8.250  -0.6486   0.10296   0.10142   0.0312   1.0000   0.0060
  -8.000  -0.6447   0.09939   0.09786   0.0296   1.0000   0.0061
  -7.750  -0.6415   0.09582   0.09430   0.0277   1.0000   0.0062
  -7.500  -0.6352   0.09198   0.09047   0.0246   1.0000   0.0063
  -7.250  -0.6247   0.08773   0.08622   0.0202   1.0000   0.0064
  -7.000  -0.6116   0.08323   0.08172   0.0151   1.0000   0.0066
  -6.750  -0.5958   0.07848   0.07696   0.0094   1.0000   0.0068
  -6.500  -0.5771   0.07347   0.07192   0.0032   1.0000   0.0071
  -6.250  -0.5554   0.06822   0.06662  -0.0033   1.0000   0.0074
  -6.000  -0.5304   0.06271   0.06105  -0.0098   1.0000   0.0081
  -5.750  -0.4942   0.05730   0.05552  -0.0166   1.0000   0.0093
  -5.500  -0.4645   0.05203   0.05012  -0.0212   1.0000   0.0094
  -5.250  -0.4349   0.04678   0.04471  -0.0250   1.0000   0.0095
  -5.000  -0.4055   0.04203   0.03976  -0.0280   1.0000   0.0095
  -4.750  -0.3761   0.03339   0.03075  -0.0331   1.0000   0.0103
  -4.500  -0.3491   0.03113   0.02837  -0.0346   1.0000   0.0108
  -4.250  -0.3197   0.02846   0.02553  -0.0360   1.0000   0.0113
  -4.000  -0.2889   0.02574   0.02260  -0.0373   1.0000   0.0121
  -3.750  -0.2574   0.02319   0.01983  -0.0382   1.0000   0.0132
  -3.500  -0.2267   0.02248   0.01899  -0.0380   1.0000   0.0151
  -3.250  -0.1956   0.02095   0.01724  -0.0384   1.0000   0.0155
  -3.000  -0.1563   0.01320   0.00864  -0.0406   1.0000   0.0117
  -2.750  -0.1260   0.01195   0.00724  -0.0410   1.0000   0.0129
  -2.500  -0.0959   0.01071   0.00586  -0.0413   1.0000   0.0132
  -2.250  -0.0664   0.00977   0.00483  -0.0415   1.0000   0.0136
  -2.000  -0.0370   0.00904   0.00406  -0.0418   1.0000   0.0141
  -1.750  -0.0072   0.00815   0.00308  -0.0422   1.0000   0.0142
  -1.500   0.0224   0.00758   0.00247  -0.0425   1.0000   0.0149
  -1.250   0.0521   0.00702   0.00184  -0.0428   1.0000   0.0203
  -1.000   0.0808   0.00689   0.00174  -0.0430   1.0000   0.0250
  -0.750   0.1097   0.00665   0.00150  -0.0432   1.0000   0.0332
  -0.500   0.1384   0.00647   0.00137  -0.0434   1.0000   0.0512
  -0.250   0.1676   0.00516   0.00131  -0.0446   1.0000   0.4855
   0.000   0.2008   0.00451   0.00149  -0.0461   0.9812   0.7520
   0.250   0.2192   0.00393   0.00140  -0.0432   0.9211   1.0000
   0.500   0.2403   0.00427   0.00136  -0.0412   0.8270   1.0000
   0.750   0.2667   0.00457   0.00136  -0.0407   0.7572   1.0000
   1.000   0.2941   0.00490   0.00138  -0.0406   0.6810   1.0000
   1.250   0.3220   0.00528   0.00143  -0.0407   0.6016   1.0000
   1.500   0.3502   0.00552   0.00151  -0.0408   0.5582   1.0000
   1.750   0.3783   0.00583   0.00159  -0.0410   0.4869   1.0000
   2.000   0.4064   0.00658   0.00175  -0.0415   0.3322   1.0000
   2.250   0.4346   0.00751   0.00202  -0.0421   0.1591   1.0000
   2.500   0.4629   0.00815   0.00227  -0.0425   0.0641   1.0000
   2.750   0.4913   0.00847   0.00250  -0.0427   0.0452   1.0000
   3.000   0.5195   0.00866   0.00272  -0.0428   0.0407   1.0000
   3.250   0.5479   0.00900   0.00305  -0.0429   0.0344   1.0000
   3.500   0.5761   0.00932   0.00341  -0.0430   0.0315   1.0000
   3.750   0.6041   0.00944   0.00352  -0.0431   0.0289   1.0000
   4.000   0.6322   0.00969   0.00378  -0.0432   0.0257   1.0000
   4.250   0.6602   0.01042   0.00462  -0.0433   0.0212   1.0000
   4.500   0.6881   0.01033   0.00449  -0.0434   0.0198   1.0000
   4.750   0.7159   0.01046   0.00459  -0.0434   0.0163   1.0000
   5.000   0.7437   0.01111   0.00530  -0.0435   0.0125   1.0000
   5.250   0.7715   0.01147   0.00570  -0.0435   0.0108   1.0000
   5.500   0.7990   0.01195   0.00622  -0.0435   0.0091   1.0000
   5.750   0.8255   0.01391   0.00847  -0.0434   0.0079   1.0000
   6.000   0.8526   0.01448   0.00913  -0.0433   0.0074   1.0000
   6.250   0.8792   0.01561   0.01042  -0.0431   0.0071   1.0000
   6.500   0.9054   0.01718   0.01222  -0.0429   0.0068   1.0000
   6.750   0.9309   0.01907   0.01438  -0.0426   0.0065   1.0000
   7.000   0.9560   0.02093   0.01654  -0.0424   0.0061   1.0000
   7.250   0.9808   0.02242   0.01825  -0.0422   0.0057   1.0000
   7.500   1.0053   0.02362   0.01962  -0.0421   0.0053   1.0000
   7.750   1.0186   0.03122   0.02808  -0.0411   0.0049   1.0000
  11.000   0.7459   0.13257   0.13114  -0.0631   0.0080   1.0000
  11.250   0.7432   0.13694   0.13551  -0.0644   0.0080   1.0000
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