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HT08 (ht08-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HT08 (ht08-il)
Reynolds number: 1,000,000
Max Cl/Cd: 63.45 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht08-il-1000000-n5.txt
Download as CSV file: xf-ht08-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT08                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7973   0.15645   0.15483   0.0647   1.0000   0.0039
 -12.250  -0.7958   0.15146   0.14985   0.0628   1.0000   0.0038
 -10.750  -1.1096   0.03377   0.03131  -0.0048   1.0000   0.0039
 -10.500  -1.0994   0.02966   0.02679  -0.0050   1.0000   0.0040
 -10.250  -1.0837   0.02676   0.02356  -0.0048   1.0000   0.0042
 -10.000  -1.0651   0.02449   0.02100  -0.0046   1.0000   0.0043
  -9.750  -1.0445   0.02267   0.01890  -0.0043   1.0000   0.0044
  -9.500  -1.0224   0.02118   0.01718  -0.0040   1.0000   0.0045
  -9.250  -0.9994   0.01987   0.01567  -0.0038   1.0000   0.0045
  -9.000  -0.9755   0.01878   0.01440  -0.0035   1.0000   0.0046
  -8.750  -0.9526   0.01717   0.01254  -0.0032   1.0000   0.0048
  -8.500  -0.9283   0.01599   0.01119  -0.0030   1.0000   0.0051
  -8.250  -0.9029   0.01523   0.01032  -0.0028   1.0000   0.0053
  -8.000  -0.8769   0.01462   0.00961  -0.0027   1.0000   0.0056
  -7.750  -0.8507   0.01407   0.00899  -0.0025   1.0000   0.0059
  -7.500  -0.8243   0.01357   0.00841  -0.0024   1.0000   0.0062
  -7.250  -0.7978   0.01306   0.00782  -0.0022   1.0000   0.0066
  -7.000  -0.7712   0.01253   0.00720  -0.0021   1.0000   0.0069
  -6.750  -0.7443   0.01206   0.00665  -0.0020   1.0000   0.0071
  -6.500  -0.7177   0.01140   0.00587  -0.0018   1.0000   0.0076
  -6.250  -0.6908   0.01088   0.00530  -0.0017   1.0000   0.0082
  -6.000  -0.6635   0.01050   0.00489  -0.0016   1.0000   0.0088
  -5.750  -0.6362   0.01016   0.00452  -0.0016   1.0000   0.0095
  -5.500  -0.6087   0.00984   0.00415  -0.0015   1.0000   0.0101
  -5.250  -0.5811   0.00958   0.00385  -0.0014   1.0000   0.0107
  -5.000  -0.5536   0.00917   0.00341  -0.0013   1.0000   0.0124
  -4.750  -0.5260   0.00889   0.00312  -0.0013   1.0000   0.0137
  -4.500  -0.4982   0.00865   0.00286  -0.0012   1.0000   0.0150
  -4.250  -0.4703   0.00841   0.00259  -0.0012   1.0000   0.0163
  -4.000  -0.4425   0.00815   0.00235  -0.0011   1.0000   0.0198
  -3.750  -0.4146   0.00795   0.00215  -0.0011   1.0000   0.0224
  -3.500  -0.3866   0.00772   0.00195  -0.0011   1.0000   0.0277
  -3.250  -0.3587   0.00754   0.00177  -0.0010   1.0000   0.0327
  -3.000  -0.3307   0.00733   0.00161  -0.0010   1.0000   0.0425
  -2.750  -0.3027   0.00713   0.00147  -0.0010   1.0000   0.0541
  -2.500  -0.2747   0.00693   0.00134  -0.0010   1.0000   0.0696
  -2.250  -0.2467   0.00671   0.00121  -0.0010   1.0000   0.0921
  -2.000  -0.2186   0.00650   0.00111  -0.0011   1.0000   0.1179
  -1.750  -0.1906   0.00629   0.00102  -0.0011   1.0000   0.1477
  -1.500  -0.1627   0.00607   0.00095  -0.0011   1.0000   0.1847
  -1.250  -0.1291   0.00589   0.00090  -0.0024   0.9582   0.2293
  -1.000  -0.1063   0.00593   0.00088  -0.0009   0.8718   0.2715
  -0.750  -0.0817   0.00605   0.00083   0.0000   0.7777   0.3187
  -0.500  -0.0550   0.00615   0.00079   0.0002   0.6863   0.3740
  -0.250  -0.0275   0.00620   0.00076   0.0001   0.5968   0.4402
   0.000   0.0001   0.00621   0.00076   0.0000   0.5152   0.5155
   0.250   0.0277   0.00619   0.00076  -0.0001   0.4412   0.5975
   0.500   0.0551   0.00615   0.00079  -0.0002   0.3735   0.6868
   0.750   0.0819   0.00605   0.00083   0.0000   0.3191   0.7779
   1.000   0.1065   0.00593   0.00088   0.0009   0.2713   0.8720
   1.250   0.1292   0.00589   0.00090   0.0024   0.2299   0.9580
   1.500   0.1628   0.00607   0.00095   0.0011   0.1844   1.0000
   1.750   0.1908   0.00630   0.00102   0.0011   0.1477   1.0000
   2.000   0.2188   0.00651   0.00111   0.0010   0.1168   1.0000
   2.250   0.2468   0.00671   0.00121   0.0010   0.0922   1.0000
   2.500   0.2748   0.00693   0.00134   0.0010   0.0696   1.0000
   2.750   0.3028   0.00713   0.00147   0.0010   0.0541   1.0000
   3.000   0.3308   0.00733   0.00161   0.0010   0.0424   1.0000
   3.250   0.3588   0.00754   0.00177   0.0010   0.0325   1.0000
   3.500   0.3868   0.00773   0.00195   0.0011   0.0277   1.0000
   3.750   0.4148   0.00795   0.00215   0.0011   0.0224   1.0000
   4.000   0.4427   0.00815   0.00235   0.0011   0.0198   1.0000
   4.250   0.4705   0.00841   0.00259   0.0012   0.0164   1.0000
   4.500   0.4984   0.00865   0.00286   0.0012   0.0149   1.0000
   4.750   0.5261   0.00889   0.00313   0.0013   0.0137   1.0000
   5.000   0.5538   0.00918   0.00341   0.0013   0.0123   1.0000
   5.250   0.5813   0.00959   0.00386   0.0014   0.0107   1.0000
   5.500   0.6089   0.00984   0.00415   0.0015   0.0101   1.0000
   5.750   0.6364   0.01016   0.00452   0.0015   0.0095   1.0000
   6.000   0.6638   0.01051   0.00490   0.0016   0.0088   1.0000
   6.250   0.6910   0.01089   0.00531   0.0017   0.0082   1.0000
   6.500   0.7180   0.01140   0.00587   0.0018   0.0076   1.0000
   6.750   0.7446   0.01207   0.00667   0.0019   0.0071   1.0000
   7.000   0.7714   0.01256   0.00723   0.0021   0.0069   1.0000
   7.250   0.7981   0.01307   0.00783   0.0022   0.0066   1.0000
   7.500   0.8246   0.01357   0.00841   0.0023   0.0062   1.0000
   7.750   0.8510   0.01407   0.00898   0.0025   0.0059   1.0000
   8.000   0.8772   0.01463   0.00962   0.0026   0.0056   1.0000
   8.250   0.9031   0.01525   0.01034   0.0028   0.0053   1.0000
   8.500   0.9287   0.01599   0.01119   0.0029   0.0051   1.0000
   8.750   0.9530   0.01716   0.01254   0.0032   0.0048   1.0000
   9.000   0.9759   0.01875   0.01437   0.0035   0.0046   1.0000
   9.250   0.9998   0.01985   0.01564   0.0037   0.0045   1.0000
   9.500   1.0229   0.02113   0.01712   0.0040   0.0045   1.0000
   9.750   1.0450   0.02264   0.01887   0.0042   0.0044   1.0000
  10.000   1.0657   0.02445   0.02095   0.0045   0.0043   1.0000
  10.250   1.0845   0.02668   0.02347   0.0047   0.0041   1.0000
  10.500   1.1004   0.02953   0.02665   0.0049   0.0040   1.0000
  10.750   1.1109   0.03357   0.03109   0.0047   0.0039   1.0000
  12.250   0.7967   0.15166   0.15004  -0.0631   0.0038   1.0000
  12.500   0.7982   0.15666   0.15504  -0.0650   0.0038   1.0000
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