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ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR07 AIRFOIL (hor07-il)
Reynolds number: 50,000
Max Cl/Cd: 43.41 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor07-il-50000-n5.txt
Download as CSV file: xf-hor07-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4062   0.11167   0.10486  -0.0056   1.0000   0.0992
  -8.000  -0.4056   0.10955   0.10282  -0.0085   1.0000   0.1016
  -7.750  -0.4058   0.10754   0.10090  -0.0121   1.0000   0.1024
  -7.500  -0.3995   0.10472   0.09815  -0.0170   1.0000   0.1028
  -7.250  -0.3881   0.10023   0.09371  -0.0174   1.0000   0.1034
  -7.000  -0.3763   0.09610   0.08962  -0.0177   1.0000   0.1042
  -6.750  -0.3648   0.09241   0.08597  -0.0191   1.0000   0.1052
  -6.500  -0.3527   0.08891   0.08250  -0.0210   1.0000   0.1067
  -6.250  -0.3283   0.08044   0.07388  -0.0369   1.0000   0.0629
  -6.000  -0.3142   0.07670   0.07016  -0.0379   1.0000   0.0623
  -5.750  -0.2980   0.07285   0.06630  -0.0403   1.0000   0.0615
  -5.500  -0.2799   0.06890   0.06236  -0.0435   1.0000   0.0603
  -5.250  -0.2594   0.06475   0.05820  -0.0474   1.0000   0.0586
  -5.000  -0.2355   0.06018   0.05358  -0.0525   1.0000   0.0567
  -4.750  -0.2080   0.05516   0.04846  -0.0584   1.0000   0.0551
  -4.500  -0.1771   0.04970   0.04280  -0.0649   1.0000   0.0537
  -4.250  -0.1443   0.04412   0.03692  -0.0711   1.0000   0.0529
  -4.000  -0.1136   0.03936   0.03176  -0.0758   1.0000   0.0530
  -3.750  -0.0893   0.03639   0.02848  -0.0780   1.0000   0.0548
  -3.500  -0.0382   0.03191   0.02317  -0.0851   0.9910   0.0601
  -3.250   0.0109   0.02812   0.01855  -0.0905   0.9824   0.0645
  -3.000   0.0546   0.02636   0.01642  -0.0943   0.9714   0.0747
  -2.750   0.0979   0.02473   0.01448  -0.0977   0.9605   0.0861
  -2.500   0.1406   0.02340   0.01281  -0.1006   0.9491   0.1047
  -2.250   0.1819   0.02261   0.01191  -0.1032   0.9373   0.1327
  -2.000   0.2207   0.02200   0.01115  -0.1053   0.9239   0.1720
  -1.750   0.2567   0.02161   0.01068  -0.1068   0.9100   0.2123
  -1.500   0.2908   0.02135   0.01031  -0.1079   0.8960   0.2533
  -1.250   0.3232   0.02103   0.00992  -0.1086   0.8824   0.2863
  -1.000   0.3545   0.02070   0.00950  -0.1090   0.8692   0.3157
  -0.750   0.3844   0.02037   0.00916  -0.1091   0.8563   0.3449
  -0.500   0.4131   0.02011   0.00896  -0.1089   0.8435   0.3818
  -0.250   0.4406   0.01969   0.00882  -0.1086   0.8311   0.4515
   0.000   0.4603   0.01841   0.00857  -0.1061   0.8176   1.0000
   0.250   0.4883   0.01867   0.00848  -0.1057   0.8036   1.0000
   0.500   0.5156   0.01893   0.00848  -0.1052   0.7898   1.0000
   0.750   0.5425   0.01919   0.00852  -0.1047   0.7761   1.0000
   1.000   0.5694   0.01946   0.00862  -0.1041   0.7628   1.0000
   1.250   0.5962   0.01975   0.00875  -0.1035   0.7502   1.0000
   1.500   0.6231   0.02003   0.00889  -0.1030   0.7387   1.0000
   1.750   0.6498   0.02035   0.00915  -0.1025   0.7264   1.0000
   2.000   0.6766   0.02071   0.00945  -0.1022   0.7140   1.0000
   2.250   0.7033   0.02106   0.00977  -0.1018   0.7023   1.0000
   2.500   0.7301   0.02140   0.01008  -0.1014   0.6914   1.0000
   2.750   0.7569   0.02176   0.01046  -0.1010   0.6798   1.0000
   3.000   0.7836   0.02217   0.01091  -0.1007   0.6674   1.0000
   3.250   0.8101   0.02257   0.01135  -0.1004   0.6555   1.0000
   3.500   0.8367   0.02293   0.01175  -0.0999   0.6444   1.0000
   3.750   0.8632   0.02328   0.01221  -0.0994   0.6337   1.0000
   4.000   0.8895   0.02376   0.01280  -0.0992   0.6218   1.0000
   4.250   0.9157   0.02420   0.01336  -0.0988   0.6108   1.0000
   4.500   0.9420   0.02455   0.01380  -0.0982   0.6004   1.0000
   4.750   0.9679   0.02496   0.01441  -0.0977   0.5886   1.0000
   5.000   0.9934   0.02546   0.01510  -0.0973   0.5765   1.0000
   5.250   1.0189   0.02588   0.01570  -0.0966   0.5643   1.0000
   5.500   1.0429   0.02576   0.01566  -0.0949   0.5430   1.0000
   5.750   1.0648   0.02540   0.01536  -0.0927   0.5105   1.0000
   6.000   1.0858   0.02535   0.01537  -0.0908   0.4719   1.0000
   6.250   1.1052   0.02546   0.01535  -0.0886   0.4204   1.0000
   6.500   1.1231   0.02609   0.01586  -0.0868   0.3475   1.0000
   6.750   1.1300   0.02838   0.01699  -0.0845   0.1828   1.0000
   7.000   1.1373   0.03139   0.01945  -0.0829   0.1251   1.0000
   7.250   1.1491   0.03356   0.02158  -0.0815   0.1039   1.0000
   7.500   1.1593   0.03567   0.02365  -0.0799   0.0936   1.0000
   7.750   1.1705   0.03753   0.02566  -0.0782   0.0874   1.0000
   8.000   1.1796   0.03952   0.02772  -0.0763   0.0833   1.0000
   8.250   1.1897   0.04144   0.02973  -0.0743   0.0802   1.0000
   8.500   1.2044   0.04308   0.03159  -0.0724   0.0773   1.0000
   8.750   1.2224   0.04470   0.03342  -0.0707   0.0741   1.0000
   9.000   1.2419   0.04644   0.03520  -0.0694   0.0702   1.0000
   9.250   1.2666   0.04843   0.03724  -0.0684   0.0664   1.0000
   9.500   1.2928   0.05053   0.03967  -0.0675   0.0640   1.0000
   9.750   1.3173   0.05311   0.04258  -0.0667   0.0621   1.0000
  10.000   1.3377   0.05607   0.04593  -0.0658   0.0604   1.0000
  10.250   1.3522   0.05912   0.04927  -0.0646   0.0582   1.0000
  10.500   1.3659   0.06251   0.05274  -0.0639   0.0553   1.0000
  10.750   1.3674   0.06622   0.05687  -0.0620   0.0537   1.0000
  11.000   1.3630   0.06996   0.06110  -0.0597   0.0529   1.0000
  11.250   1.3515   0.07362   0.06518  -0.0573   0.0520   1.0000
  11.500   1.3352   0.07739   0.06929  -0.0550   0.0514   1.0000
  11.750   1.3172   0.08170   0.07391  -0.0540   0.0508   1.0000
  12.000   1.2975   0.08661   0.07911  -0.0541   0.0505   1.0000
  12.250   1.2762   0.09220   0.08496  -0.0554   0.0504   1.0000
  12.500   1.2535   0.09852   0.09152  -0.0577   0.0506   1.0000
  12.750   1.2297   0.10566   0.09886  -0.0610   0.0510   1.0000
  13.000   1.2056   0.11359   0.10696  -0.0654   0.0515   1.0000
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