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ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR07 AIRFOIL (hor07-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.38 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor07-il-1000000-n5.txt
Download as CSV file: xf-hor07-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4522   0.10229   0.09810   0.0020   0.1790   0.0075
  -8.250  -0.4474   0.09847   0.09429   0.0000   0.1786   0.0077
  -8.000  -0.4431   0.09463   0.09046  -0.0021   0.1783   0.0078
  -7.000  -0.3772   0.02322   0.01769  -0.0824   0.1788   0.0082
  -6.750  -0.3465   0.02088   0.01496  -0.0845   0.1783   0.0083
  -6.500  -0.3163   0.01921   0.01298  -0.0859   0.1779   0.0083
  -6.250  -0.2863   0.01792   0.01141  -0.0869   0.1771   0.0084
  -6.000  -0.2568   0.01709   0.01039  -0.0876   0.1764   0.0084
  -5.750  -0.2273   0.01639   0.00952  -0.0882   0.1760   0.0085
  -5.500  -0.1976   0.01554   0.00846  -0.0888   0.1756   0.0086
  -5.250  -0.1676   0.01468   0.00740  -0.0894   0.1753   0.0086
  -5.000  -0.1377   0.01394   0.00649  -0.0900   0.1750   0.0087
  -4.750  -0.1079   0.01334   0.00573  -0.0904   0.1747   0.0088
  -4.500  -0.0782   0.01285   0.00512  -0.0908   0.1744   0.0090
  -4.250  -0.0487   0.01246   0.00462  -0.0912   0.1742   0.0092
  -4.000  -0.0193   0.01214   0.00422  -0.0914   0.1739   0.0095
  -3.750   0.0100   0.01190   0.00391  -0.0917   0.1736   0.0100
  -3.500   0.0393   0.01169   0.00365  -0.0919   0.1734   0.0104
  -3.250   0.0685   0.01152   0.00341  -0.0921   0.1732   0.0108
  -3.000   0.0976   0.01137   0.00320  -0.0923   0.1729   0.0113
  -2.750   0.1267   0.01124   0.00303  -0.0924   0.1727   0.0118
  -2.500   0.1559   0.01111   0.00286  -0.0926   0.1726   0.0129
  -2.000   0.2140   0.01090   0.00262  -0.0930   0.1722   0.0200
  -1.750   0.2431   0.01080   0.00254  -0.0931   0.1721   0.0274
  -1.500   0.2721   0.01071   0.00246  -0.0933   0.1720   0.0374
  -1.250   0.3011   0.01065   0.00240  -0.0935   0.1719   0.0455
  -1.000   0.3301   0.01056   0.00235  -0.0937   0.1718   0.0625
  -0.750   0.3591   0.01045   0.00233  -0.0939   0.1718   0.0956
  -0.500   0.3879   0.01046   0.00232  -0.0940   0.1717   0.1038
  -0.250   0.4169   0.01041   0.00233  -0.0942   0.1716   0.1205
   0.000   0.4457   0.01039   0.00235  -0.0943   0.1715   0.1368
   0.250   0.4745   0.01038   0.00237  -0.0945   0.1715   0.1523
   0.500   0.5033   0.01039   0.00239  -0.0946   0.1714   0.1643
   1.000   0.5607   0.01042   0.00247  -0.0949   0.1714   0.1898
   1.250   0.5894   0.01042   0.00254  -0.0950   0.1714   0.2131
   1.500   0.6181   0.01044   0.00259  -0.0952   0.1714   0.2307
   1.750   0.6467   0.01047   0.00266  -0.0953   0.1714   0.2453
   2.000   0.6753   0.01051   0.00274  -0.0954   0.1705   0.2621
   2.250   0.7039   0.01057   0.00285  -0.0956   0.1671   0.2855
   2.500   0.7324   0.01065   0.00297  -0.0957   0.1632   0.3130
   2.750   0.7610   0.01062   0.00301  -0.0958   0.1595   0.3346
   3.000   0.7895   0.01070   0.00310  -0.0960   0.1422   0.3905
   3.250   0.8178   0.01083   0.00324  -0.0961   0.1373   0.4039
   3.500   0.8460   0.01096   0.00343  -0.0963   0.1330   0.4174
   3.750   0.8746   0.01092   0.00364  -0.0966   0.1289   0.5351
   4.000   0.8968   0.01028   0.00382  -0.0956   0.0847   1.0000
   4.250   0.9243   0.01066   0.00409  -0.0956   0.0610   1.0000
   4.500   0.9518   0.01101   0.00435  -0.0957   0.0448   1.0000
   4.750   0.9793   0.01132   0.00459  -0.0957   0.0329   1.0000
   5.000   1.0068   0.01159   0.00482  -0.0957   0.0284   1.0000
   5.250   1.0343   0.01187   0.00507  -0.0957   0.0252   1.0000
   5.500   1.0617   0.01213   0.00535  -0.0957   0.0236   1.0000
   5.750   1.0890   0.01239   0.00562  -0.0957   0.0231   1.0000
   6.000   1.1162   0.01265   0.00591  -0.0957   0.0226   1.0000
   6.250   1.1433   0.01294   0.00621  -0.0956   0.0220   1.0000
   6.500   1.1701   0.01324   0.00655  -0.0956   0.0215   1.0000
   6.750   1.1968   0.01355   0.00686  -0.0955   0.0205   1.0000
   7.000   1.2232   0.01389   0.00720  -0.0954   0.0193   1.0000
   7.250   1.2493   0.01428   0.00761  -0.0953   0.0183   1.0000
   7.500   1.2750   0.01474   0.00812  -0.0951   0.0175   1.0000
   7.750   1.3007   0.01516   0.00858  -0.0949   0.0171   1.0000
   8.000   1.3265   0.01550   0.00894  -0.0947   0.0169   1.0000
   8.250   1.3522   0.01583   0.00930  -0.0945   0.0166   1.0000
   8.500   1.3777   0.01616   0.00966  -0.0943   0.0161   1.0000
   8.750   1.4031   0.01649   0.01004  -0.0941   0.0153   1.0000
   9.000   1.4282   0.01684   0.01040  -0.0939   0.0144   1.0000
   9.250   1.4529   0.01722   0.01078  -0.0936   0.0133   1.0000
   9.500   1.4768   0.01769   0.01126  -0.0932   0.0123   1.0000
   9.750   1.5011   0.01809   0.01170  -0.0928   0.0116   1.0000
  10.000   1.5248   0.01852   0.01216  -0.0924   0.0087   1.0000
  10.250   1.5465   0.01919   0.01277  -0.0918   0.0064   1.0000
  10.500   1.5679   0.01985   0.01348  -0.0911   0.0056   1.0000
  10.750   1.5884   0.02058   0.01427  -0.0902   0.0052   1.0000
  11.000   1.6079   0.02136   0.01512  -0.0892   0.0048   1.0000
  11.250   1.6264   0.02219   0.01602  -0.0881   0.0045   1.0000
  11.500   1.6436   0.02308   0.01700  -0.0868   0.0041   1.0000
  11.750   1.6603   0.02394   0.01794  -0.0855   0.0039   1.0000
  12.000   1.6758   0.02480   0.01888  -0.0840   0.0038   1.0000
  12.250   1.6893   0.02572   0.01989  -0.0822   0.0037   1.0000
  12.500   1.7005   0.02673   0.02099  -0.0801   0.0037   1.0000
  12.750   1.7079   0.02785   0.02221  -0.0776   0.0036   1.0000
  13.000   1.7108   0.02918   0.02364  -0.0746   0.0035   1.0000
  13.250   1.7145   0.03073   0.02530  -0.0723   0.0034   1.0000
  13.500   1.7181   0.03252   0.02720  -0.0706   0.0033   1.0000
  13.750   1.7216   0.03454   0.02932  -0.0693   0.0033   1.0000
  14.000   1.7244   0.03678   0.03169  -0.0683   0.0032   1.0000
  14.250   1.7265   0.03924   0.03426  -0.0675   0.0031   1.0000
  14.500   1.7275   0.04192   0.03706  -0.0670   0.0031   1.0000
  14.750   1.7273   0.04481   0.04006  -0.0666   0.0030   1.0000
  15.000   1.7257   0.04795   0.04332  -0.0663   0.0030   1.0000
  15.250   1.7223   0.05132   0.04681  -0.0662   0.0029   1.0000
  15.500   1.7175   0.05498   0.05059  -0.0662   0.0029   1.0000
  15.750   1.7114   0.05887   0.05461  -0.0665   0.0028   1.0000
  16.000   1.7033   0.06308   0.05895  -0.0669   0.0028   1.0000
  16.250   1.6941   0.06757   0.06357  -0.0675   0.0028   1.0000
  16.500   1.6836   0.07240   0.06852  -0.0684   0.0027   1.0000
  16.750   1.6720   0.07759   0.07384  -0.0696   0.0027   1.0000
  17.000   1.6597   0.08311   0.07950  -0.0712   0.0027   1.0000
  17.250   1.6465   0.08897   0.08550  -0.0730   0.0027   1.0000
  17.500   1.6316   0.09523   0.09189  -0.0752   0.0026   1.0000
  17.750   1.6162   0.10174   0.09853  -0.0776   0.0026   1.0000
  18.000   1.5997   0.10862   0.10555  -0.0803   0.0026   1.0000
  18.250   1.5816   0.11593   0.11300  -0.0835   0.0026   1.0000
  18.500   1.5629   0.12357   0.12078  -0.0869   0.0026   1.0000
  18.750   1.5441   0.13147   0.12882  -0.0908   0.0026   1.0000
  19.000   1.5246   0.13974   0.13722  -0.0951   0.0026   1.0000
  19.250   1.5033   0.14871   0.14634  -0.1000   0.0026   1.0000
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