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ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR07 AIRFOIL (hor07-il)
Reynolds number: 500,000
Max Cl/Cd: 80.52 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor07-il-500000-n5.txt
Download as CSV file: xf-hor07-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA HOR07 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3392   0.08058   0.07765  -0.0128   0.7168   0.0117
  -7.750  -0.3365   0.07681   0.07385  -0.0139   0.7098   0.0115
  -7.500  -0.4266   0.08730   0.08428  -0.0068   0.7238   0.0115
  -7.250  -0.4158   0.08345   0.08040  -0.0105   0.7149   0.0113
  -7.000  -0.4029   0.07910   0.07601  -0.0152   0.7071   0.0112
  -6.750  -0.3871   0.07415   0.07102  -0.0210   0.6997   0.0111
  -6.500  -0.3677   0.06846   0.06527  -0.0282   0.6921   0.0111
  -6.000  -0.2657   0.02337   0.01862  -0.0819   0.6845   0.0112
  -5.750  -0.2328   0.02007   0.01469  -0.0847   0.6710   0.0114
  -5.500  -0.2015   0.01799   0.01212  -0.0863   0.6556   0.0114
  -5.250  -0.1709   0.01654   0.01029  -0.0873   0.6408   0.0114
  -5.000  -0.1407   0.01544   0.00889  -0.0880   0.6279   0.0115
  -4.750  -0.1107   0.01458   0.00777  -0.0885   0.6153   0.0116
  -4.500  -0.0809   0.01390   0.00686  -0.0890   0.6007   0.0118
  -4.250  -0.0511   0.01327   0.00606  -0.0894   0.5894   0.0120
  -4.000  -0.0211   0.01260   0.00524  -0.0899   0.5796   0.0125
  -3.750   0.0084   0.01221   0.00474  -0.0903   0.5707   0.0131
  -3.500   0.0379   0.01191   0.00433  -0.0906   0.5595   0.0138
  -3.250   0.0672   0.01164   0.00395  -0.0908   0.5480   0.0146
  -3.000   0.0966   0.01142   0.00362  -0.0910   0.5345   0.0156
  -2.750   0.1260   0.01120   0.00329  -0.0913   0.5207   0.0171
  -2.500   0.1551   0.01104   0.00305  -0.0915   0.5049   0.0206
  -2.250   0.1843   0.01089   0.00284  -0.0917   0.4870   0.0276
  -2.000   0.2134   0.01080   0.00267  -0.0920   0.4678   0.0366
  -1.750   0.2425   0.01072   0.00253  -0.0922   0.4513   0.0459
  -1.500   0.2715   0.01061   0.00240  -0.0924   0.4397   0.0615
  -1.250   0.3006   0.01047   0.00234  -0.0927   0.4314   0.0960
  -0.750   0.3585   0.01037   0.00227  -0.0931   0.4176   0.1356
  -0.500   0.3874   0.01035   0.00225  -0.0932   0.4107   0.1505
  -0.250   0.4162   0.01034   0.00224  -0.0934   0.4037   0.1656
   0.000   0.4451   0.01032   0.00224  -0.0935   0.3974   0.1815
   0.250   0.4739   0.01032   0.00225  -0.0937   0.3908   0.1956
   0.500   0.5027   0.01032   0.00227  -0.0938   0.3851   0.2157
   0.750   0.5315   0.01032   0.00231  -0.0940   0.3784   0.2367
   1.000   0.5603   0.01034   0.00235  -0.0941   0.3723   0.2543
   1.250   0.5890   0.01034   0.00240  -0.0943   0.3664   0.2759
   1.500   0.6177   0.01036   0.00246  -0.0945   0.3600   0.3042
   1.750   0.6464   0.01037   0.00253  -0.0946   0.3542   0.3327
   2.250   0.7038   0.01033   0.00272  -0.0951   0.3430   0.4296
   2.500   0.7254   0.00915   0.00274  -0.0937   0.3386   1.0000
   2.750   0.7537   0.00936   0.00287  -0.0938   0.3241   1.0000
   3.000   0.7815   0.00973   0.00305  -0.0939   0.2903   1.0000
   3.250   0.8078   0.01064   0.00344  -0.0942   0.1880   1.0000
   3.500   0.8355   0.01099   0.00370  -0.0942   0.1767   1.0000
   3.750   0.8634   0.01124   0.00393  -0.0943   0.1721   1.0000
   4.000   0.8913   0.01144   0.00414  -0.0944   0.1660   1.0000
   4.250   0.9192   0.01166   0.00430  -0.0944   0.1427   1.0000
   4.500   0.9465   0.01206   0.00463  -0.0944   0.1304   1.0000
   4.750   0.9730   0.01265   0.00503  -0.0945   0.0749   1.0000
   5.000   0.9997   0.01314   0.00542  -0.0944   0.0530   1.0000
   5.250   1.0265   0.01354   0.00577  -0.0944   0.0411   1.0000
   5.500   1.0533   0.01393   0.00613  -0.0943   0.0343   1.0000
   5.750   1.0801   0.01430   0.00652  -0.0942   0.0310   1.0000
   6.000   1.1067   0.01467   0.00692  -0.0941   0.0294   1.0000
   6.250   1.1330   0.01507   0.00734  -0.0940   0.0281   1.0000
   6.500   1.1591   0.01550   0.00780  -0.0938   0.0270   1.0000
   6.750   1.1848   0.01598   0.00833  -0.0936   0.0260   1.0000
   7.000   1.2100   0.01652   0.00893  -0.0933   0.0251   1.0000
   7.250   1.2343   0.01719   0.00967  -0.0929   0.0242   1.0000
   7.500   1.2587   0.01778   0.01032  -0.0926   0.0234   1.0000
   7.750   1.2836   0.01821   0.01081  -0.0923   0.0228   1.0000
   8.000   1.3080   0.01870   0.01136  -0.0919   0.0220   1.0000
   8.250   1.3320   0.01922   0.01195  -0.0915   0.0211   1.0000
   8.500   1.3553   0.01980   0.01259  -0.0910   0.0204   1.0000
   8.750   1.3781   0.02042   0.01328  -0.0904   0.0198   1.0000
   9.000   1.4006   0.02101   0.01393  -0.0899   0.0190   1.0000
   9.250   1.4220   0.02172   0.01467  -0.0892   0.0180   1.0000
   9.500   1.4408   0.02270   0.01572  -0.0882   0.0171   1.0000
   9.750   1.4636   0.02311   0.01621  -0.0876   0.0165   1.0000
  10.000   1.4858   0.02357   0.01675  -0.0870   0.0155   1.0000
  10.250   1.5074   0.02405   0.01731  -0.0863   0.0143   1.0000
  10.500   1.5287   0.02453   0.01782  -0.0856   0.0131   1.0000
  10.750   1.5477   0.02522   0.01854  -0.0846   0.0120   1.0000
  11.000   1.5655   0.02596   0.01940  -0.0835   0.0105   1.0000
  11.250   1.5831   0.02663   0.02010  -0.0823   0.0087   1.0000
  11.500   1.5970   0.02755   0.02106  -0.0807   0.0079   1.0000
  11.750   1.6080   0.02863   0.02219  -0.0787   0.0072   1.0000
  12.000   1.6141   0.02987   0.02353  -0.0761   0.0067   1.0000
  12.250   1.6173   0.03137   0.02513  -0.0734   0.0064   1.0000
  12.500   1.6203   0.03314   0.02700  -0.0713   0.0061   1.0000
  12.750   1.6234   0.03513   0.02913  -0.0697   0.0059   1.0000
  13.000   1.6260   0.03736   0.03150  -0.0685   0.0058   1.0000
  13.250   1.6281   0.03979   0.03407  -0.0676   0.0056   1.0000
  13.500   1.6294   0.04243   0.03686  -0.0669   0.0055   1.0000
  13.750   1.6296   0.04528   0.03986  -0.0664   0.0053   1.0000
  14.000   1.6288   0.04833   0.04305  -0.0661   0.0052   1.0000
  14.250   1.6267   0.05159   0.04645  -0.0659   0.0051   1.0000
  14.500   1.6232   0.05508   0.05009  -0.0659   0.0050   1.0000
  14.750   1.6187   0.05880   0.05395  -0.0660   0.0048   1.0000
  15.000   1.6123   0.06282   0.05811  -0.0663   0.0047   1.0000
  15.250   1.6045   0.06715   0.06261  -0.0669   0.0047   1.0000
  15.500   1.5954   0.07177   0.06738  -0.0677   0.0046   1.0000
  15.750   1.5850   0.07670   0.07245  -0.0687   0.0045   1.0000
  16.000   1.5736   0.08207   0.07797  -0.0702   0.0045   1.0000
  16.250   1.5617   0.08774   0.08380  -0.0719   0.0044   1.0000
  16.500   1.5484   0.09379   0.09000  -0.0740   0.0044   1.0000
  16.750   1.5342   0.10022   0.09659  -0.0765   0.0043   1.0000
  17.000   1.5191   0.10698   0.10350  -0.0792   0.0043   1.0000
  17.250   1.5034   0.11402   0.11070  -0.0823   0.0043   1.0000
  17.500   1.4866   0.12148   0.11832  -0.0857   0.0043   1.0000
  17.750   1.4695   0.12930   0.12629  -0.0896   0.0043   1.0000
  18.000   1.4517   0.13751   0.13465  -0.0939   0.0043   1.0000
  18.250   1.4325   0.14634   0.14364  -0.0988   0.0043   1.0000
  18.500   1.4117   0.15616   0.15362  -0.1045   0.0043   1.0000
  18.750   1.3882   0.16735   0.16500  -0.1112   0.0044   1.0000
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