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ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR04 AIRFOIL (hor04-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.94 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor04-il-1000000-n5.txt
Download as CSV file: xf-hor04-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5316   0.10683   0.10534   0.0228   1.0000   0.0046
  -9.000  -0.5290   0.10316   0.10167   0.0217   1.0000   0.0052
  -8.750  -0.6640   0.10800   0.10645   0.0349   1.0000   0.0036
  -8.500  -0.6585   0.10514   0.10360   0.0336   1.0000   0.0038
  -8.250  -0.6520   0.10252   0.10098   0.0322   1.0000   0.0040
  -8.000  -0.6469   0.09935   0.09782   0.0304   1.0000   0.0043
  -7.750  -0.6428   0.09596   0.09444   0.0284   1.0000   0.0047
  -7.500  -0.6368   0.09198   0.09048   0.0251   1.0000   0.0050
  -7.250  -0.6265   0.08715   0.08565   0.0201   1.0000   0.0049
  -7.000  -0.6134   0.08170   0.08019   0.0138   1.0000   0.0047
  -6.750  -0.5967   0.07599   0.07446   0.0069   1.0000   0.0047
  -6.500  -0.5763   0.07010   0.06854  -0.0003   1.0000   0.0049
  -6.250  -0.5523   0.06395   0.06232  -0.0076   1.0000   0.0055
  -6.000  -0.5237   0.05757   0.05583  -0.0146   1.0000   0.0061
  -5.750  -0.4931   0.05329   0.05142  -0.0189   1.0000   0.0066
  -5.500  -0.4636   0.04864   0.04663  -0.0229   1.0000   0.0067
  -4.750  -0.3762   0.03255   0.02988  -0.0331   1.0000   0.0062
  -4.500  -0.3438   0.02769   0.02470  -0.0353   1.0000   0.0060
  -4.250  -0.3105   0.02314   0.01977  -0.0370   1.0000   0.0058
  -4.000  -0.2753   0.01808   0.01419  -0.0384   1.0000   0.0056
  -3.750  -0.2396   0.01266   0.00806  -0.0397   1.0000   0.0059
  -3.500  -0.2100   0.01155   0.00678  -0.0400   1.0000   0.0064
  -3.250  -0.1812   0.01108   0.00622  -0.0403   1.0000   0.0066
  -3.000  -0.1510   0.00947   0.00439  -0.0409   1.0000   0.0074
  -2.750  -0.1220   0.00893   0.00380  -0.0412   1.0000   0.0079
  -2.500  -0.0929   0.00849   0.00332  -0.0415   1.0000   0.0082
  -2.250  -0.0639   0.00811   0.00291  -0.0418   1.0000   0.0086
  -2.000  -0.0351   0.00786   0.00266  -0.0420   1.0000   0.0092
  -1.750  -0.0044   0.00757   0.00232  -0.0426   0.9859   0.0096
  -1.500   0.0253   0.00737   0.00205  -0.0429   0.9602   0.0098
  -1.250   0.0499   0.00732   0.00190  -0.0419   0.9213   0.0103
  -1.000   0.0744   0.00734   0.00176  -0.0408   0.8792   0.0114
  -0.750   0.1009   0.00737   0.00167  -0.0404   0.8367   0.0189
  -0.500   0.1282   0.00744   0.00159  -0.0402   0.7977   0.0217
  -0.250   0.1560   0.00752   0.00154  -0.0401   0.7549   0.0277
   0.000   0.1840   0.00765   0.00150  -0.0402   0.6909   0.0464
   0.250   0.2136   0.00719   0.00148  -0.0411   0.6157   0.3173
   0.500   0.2424   0.00694   0.00154  -0.0418   0.5725   0.4920
   0.750   0.2709   0.00697   0.00157  -0.0421   0.5007   0.5776
   1.000   0.2991   0.00701   0.00165  -0.0426   0.4171   0.6985
   1.250   0.3220   0.00690   0.00173  -0.0417   0.2835   0.9105
   1.500   0.3490   0.00723   0.00173  -0.0417   0.1728   1.0000
   1.750   0.3774   0.00766   0.00189  -0.0421   0.0981   1.0000
   2.000   0.4058   0.00794   0.00202  -0.0423   0.0638   1.0000
   2.250   0.4341   0.00814   0.00214  -0.0424   0.0482   1.0000
   2.500   0.4624   0.00833   0.00228  -0.0426   0.0390   1.0000
   2.750   0.4907   0.00848   0.00242  -0.0427   0.0357   1.0000
   3.000   0.5189   0.00867   0.00261  -0.0428   0.0322   1.0000
   3.250   0.5471   0.00889   0.00281  -0.0429   0.0272   1.0000
   3.500   0.5752   0.00904   0.00296  -0.0430   0.0256   1.0000
   3.750   0.6032   0.00923   0.00315  -0.0431   0.0230   1.0000
   4.000   0.6313   0.00945   0.00336  -0.0432   0.0200   1.0000
   4.250   0.6593   0.00972   0.00365  -0.0433   0.0172   1.0000
   4.500   0.6872   0.00990   0.00386  -0.0434   0.0145   1.0000
   4.750   0.7150   0.01022   0.00414  -0.0435   0.0100   1.0000
   5.000   0.7428   0.01052   0.00448  -0.0435   0.0090   1.0000
   5.250   0.7705   0.01087   0.00487  -0.0436   0.0081   1.0000
   5.500   0.7981   0.01125   0.00528  -0.0437   0.0074   1.0000
   5.750   0.8256   0.01173   0.00585  -0.0437   0.0065   1.0000
   6.000   0.8527   0.01271   0.00700  -0.0437   0.0055   1.0000
   6.250   0.8798   0.01323   0.00760  -0.0436   0.0054   1.0000
   6.500   0.9069   0.01366   0.00810  -0.0437   0.0051   1.0000
   6.750   0.9336   0.01431   0.00886  -0.0436   0.0048   1.0000
   7.000   0.9600   0.01510   0.00978  -0.0435   0.0045   1.0000
   7.250   0.9862   0.01597   0.01079  -0.0434   0.0042   1.0000
   7.500   1.0122   0.01682   0.01182  -0.0433   0.0040   1.0000
   7.750   1.0380   0.01764   0.01276  -0.0432   0.0037   1.0000
   8.000   1.0636   0.01841   0.01365  -0.0431   0.0035   1.0000
   8.250   1.0886   0.01940   0.01477  -0.0430   0.0032   1.0000
   8.500   1.1087   0.02299   0.01891  -0.0425   0.0027   1.0000
   8.750   1.1320   0.02440   0.02053  -0.0422   0.0027   1.0000
   9.000   1.1536   0.02636   0.02276  -0.0419   0.0025   1.0000
   9.250   1.1718   0.02951   0.02628  -0.0414   0.0024   1.0000
  10.250   0.9634   0.11368   0.11227  -0.0756   0.0027   1.0000
  10.500   0.9540   0.12093   0.11950  -0.0791   0.0027   1.0000
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