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ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR07 AIRFOIL (hor07-il)
Reynolds number: 50,000
Max Cl/Cd: 43.72 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor07-il-50000.txt
Download as CSV file: xf-hor07-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3898   0.10436   0.09779  -0.0059   1.0000   0.1644
  -7.250  -0.3877   0.10233   0.09584  -0.0080   1.0000   0.1704
  -7.000  -0.3848   0.10034   0.09396  -0.0134   1.0000   0.1737
  -6.750  -0.3689   0.09522   0.08885  -0.0106   1.0000   0.1795
  -6.500  -0.3628   0.09432   0.08802  -0.0191   1.0000   0.1875
  -6.250  -0.3499   0.08900   0.08275  -0.0160   1.0000   0.1917
  -6.000  -0.3373   0.08716   0.08095  -0.0228   1.0000   0.2024
  -5.750  -0.3258   0.08244   0.07631  -0.0196   1.0000   0.2087
  -5.500  -0.3118   0.07971   0.07361  -0.0250   1.0000   0.2197
  -5.250  -0.2945   0.07728   0.07120  -0.0304   1.0000   0.2331
  -5.000  -0.2864   0.07305   0.06709  -0.0257   1.0000   0.2398
  -4.750  -0.2730   0.07015   0.06425  -0.0286   1.0000   0.2512
  -4.500  -0.2604   0.06762   0.06177  -0.0311   1.0000   0.2645
  -4.250  -0.2499   0.06535   0.05954  -0.0326   1.0000   0.2787
  -4.000  -0.2486   0.06284   0.05713  -0.0291   1.0000   0.2868
  -3.750  -0.2416   0.06062   0.05496  -0.0291   1.0000   0.3004
  -3.500  -0.2274   0.05853   0.05284  -0.0319   1.0000   0.3232
  -3.250  -0.2223   0.05613   0.05049  -0.0294   1.0000   0.3409
  -2.750  -0.0959   0.04539   0.03876  -0.0608   1.0000   0.2221
  -2.500  -0.0167   0.03683   0.02893  -0.0758   1.0000   0.1538
  -2.250   0.0244   0.03360   0.02489  -0.0803   1.0000   0.1577
  -2.000   0.0505   0.03210   0.02329  -0.0813   1.0000   0.1689
  -1.750   0.0834   0.03048   0.02123  -0.0834   1.0000   0.1852
  -1.500   0.1107   0.02959   0.02021  -0.0844   1.0000   0.2102
  -1.250   0.1399   0.02876   0.01914  -0.0857   1.0000   0.2441
  -1.000   0.1677   0.02810   0.01838  -0.0868   1.0000   0.2886
  -0.750   0.2149   0.02732   0.01751  -0.0912   0.9925   0.3595
  -0.500   0.2692   0.02664   0.01675  -0.0967   0.9819   0.4285
  -0.250   0.3232   0.02594   0.01616  -0.1020   0.9704   0.4981
   0.000   0.3688   0.02431   0.01560  -0.1053   0.9587   0.6836
   0.250   0.4201   0.02431   0.01506  -0.1101   0.9416   1.0000
   0.500   0.4704   0.02467   0.01503  -0.1147   0.9265   1.0000
   0.750   0.5185   0.02502   0.01512  -0.1187   0.9117   1.0000
   1.000   0.5603   0.02542   0.01536  -0.1215   0.8969   1.0000
   1.250   0.5985   0.02588   0.01572  -0.1234   0.8823   1.0000
   1.500   0.6335   0.02641   0.01617  -0.1248   0.8677   1.0000
   1.750   0.6659   0.02702   0.01673  -0.1257   0.8533   1.0000
   2.000   0.6960   0.02770   0.01741  -0.1261   0.8389   1.0000
   2.250   0.7242   0.02846   0.01816  -0.1262   0.8247   1.0000
   2.500   0.7507   0.02932   0.01904  -0.1262   0.8110   1.0000
   2.750   0.7763   0.03029   0.02004  -0.1262   0.7982   1.0000
   3.000   0.8024   0.03125   0.02108  -0.1261   0.7861   1.0000
   3.250   0.8327   0.03190   0.02178  -0.1261   0.7757   1.0000
   3.500   0.8542   0.03316   0.02312  -0.1257   0.7626   1.0000
   3.750   0.8744   0.03460   0.02466  -0.1254   0.7502   1.0000
   4.000   0.8954   0.03604   0.02625  -0.1252   0.7388   1.0000
   4.250   0.9217   0.03698   0.02731  -0.1248   0.7284   1.0000
   4.500   0.9471   0.03780   0.02827  -0.1239   0.7164   1.0000
   4.750   0.9664   0.03916   0.02978  -0.1231   0.7029   1.0000
   5.000   0.9844   0.04072   0.03151  -0.1224   0.6900   1.0000
   5.250   1.0034   0.04220   0.03322  -0.1216   0.6778   1.0000
   5.500   1.0265   0.04291   0.03414  -0.1201   0.6634   1.0000
   5.750   1.0647   0.03981   0.03122  -0.1145   0.6376   1.0000
   6.000   1.0978   0.03521   0.02674  -0.1064   0.6007   1.0000
   6.250   1.1262   0.03149   0.02302  -0.0996   0.5648   1.0000
   6.500   1.1481   0.02884   0.02049  -0.0939   0.5190   1.0000
   6.750   1.1590   0.02651   0.01791  -0.0866   0.4001   1.0000
   7.000   1.1556   0.02947   0.01912  -0.0819   0.2124   1.0000
   7.250   1.1626   0.03252   0.02156  -0.0795   0.1799   1.0000
   7.500   1.1790   0.03482   0.02376  -0.0773   0.1624   1.0000
   7.750   1.2019   0.03677   0.02568  -0.0758   0.1498   1.0000
   8.000   1.2282   0.03883   0.02763  -0.0747   0.1391   1.0000
   8.250   1.2607   0.04133   0.02996  -0.0744   0.1315   1.0000
   8.500   1.2899   0.04406   0.03307  -0.0737   0.1277   1.0000
   8.750   1.3157   0.04711   0.03653  -0.0728   0.1248   1.0000
   9.000   1.3409   0.05049   0.03999  -0.0723   0.1197   1.0000
   9.250   1.3578   0.05427   0.04426  -0.0710   0.1170   1.0000
   9.500   1.3720   0.05848   0.04904  -0.0694   0.1166   1.0000
   9.750   1.3799   0.06298   0.05413  -0.0676   0.1164   1.0000
  10.000   1.3792   0.06755   0.05933  -0.0655   0.1156   1.0000
  10.250   1.3729   0.07232   0.06461  -0.0635   0.1152   1.0000
  10.500   1.3620   0.07735   0.07005  -0.0616   0.1155   1.0000
  10.750   1.3489   0.08262   0.07565  -0.0600   0.1165   1.0000
  11.000   1.3402   0.08831   0.08154  -0.0590   0.1179   1.0000
  11.250   1.3041   0.09283   0.08635  -0.0573   0.1197   1.0000
  11.500   1.2251   0.10259   0.09635  -0.0627   0.1275   1.0000
  11.750   1.2069   0.11043   0.10424  -0.0657   0.1297   1.0000
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