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HT05 (ht05-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HT05 (ht05-il)
Reynolds number: 50,000
Max Cl/Cd: 19.18 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ht05-il-50000.txt
Download as CSV file: xf-ht05-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT05                                            
  
 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  -0.6933   0.09726   0.09062   0.0385   1.0000   0.2748
  -7.250  -0.6955   0.09383   0.08726   0.0374   1.0000   0.2874
  -7.000  -0.6905   0.08997   0.08340   0.0371   1.0000   0.3020
  -6.750  -0.6829   0.08605   0.07949   0.0376   1.0000   0.3179
  -6.500  -0.6825   0.08300   0.07649   0.0365   1.0000   0.3412
  -6.250  -0.6734   0.07941   0.07292   0.0390   1.0000   0.3695
  -5.750  -0.6242   0.05143   0.04329  -0.0061   1.0000   0.1412
  -5.500  -0.6037   0.04659   0.03810  -0.0069   1.0000   0.1399
  -5.250  -0.5813   0.04186   0.03285  -0.0074   1.0000   0.1374
  -5.000  -0.5568   0.03726   0.02760  -0.0077   1.0000   0.1347
  -4.750  -0.5311   0.03361   0.02331  -0.0075   1.0000   0.1374
  -4.500  -0.5060   0.03099   0.02034  -0.0070   1.0000   0.1490
  -4.250  -0.4783   0.02815   0.01689  -0.0064   1.0000   0.1581
  -4.000  -0.4523   0.02607   0.01471  -0.0057   1.0000   0.1763
  -3.750  -0.4253   0.02409   0.01251  -0.0049   1.0000   0.2019
  -3.500  -0.3990   0.02233   0.01077  -0.0041   1.0000   0.2427
  -3.250  -0.3724   0.02049   0.00922  -0.0031   1.0000   0.3037
  -3.000  -0.3470   0.01869   0.00798  -0.0019   1.0000   0.4042
  -2.750  -0.3286   0.01713   0.00737   0.0012   1.0000   0.5604
  -2.500  -0.2469   0.01476   0.00569  -0.0066   1.0000   1.0000
  -2.250  -0.2219   0.01462   0.00511  -0.0062   1.0000   1.0000
  -2.000  -0.1971   0.01452   0.00467  -0.0056   1.0000   1.0000
  -1.750  -0.1725   0.01443   0.00431  -0.0050   1.0000   1.0000
  -1.500  -0.1478   0.01436   0.00399  -0.0043   1.0000   1.0000
  -1.250  -0.1232   0.01430   0.00375  -0.0036   1.0000   1.0000
  -1.000  -0.0986   0.01425   0.00356  -0.0029   1.0000   1.0000
  -0.750  -0.0739   0.01422   0.00342  -0.0022   1.0000   1.0000
  -0.500  -0.0493   0.01419   0.00331  -0.0014   1.0000   1.0000
  -0.250  -0.0246   0.01418   0.00325  -0.0007   1.0000   1.0000
   0.000   0.0001   0.01417   0.00323   0.0000   1.0000   1.0000
   0.250   0.0247   0.01418   0.00325   0.0007   1.0000   1.0000
   0.500   0.0494   0.01419   0.00331   0.0014   1.0000   1.0000
   0.750   0.0740   0.01422   0.00342   0.0022   1.0000   1.0000
   1.000   0.0987   0.01425   0.00356   0.0029   1.0000   1.0000
   1.250   0.1233   0.01430   0.00375   0.0036   1.0000   1.0000
   1.500   0.1480   0.01436   0.00399   0.0043   1.0000   1.0000
   1.750   0.1726   0.01443   0.00431   0.0050   1.0000   1.0000
   2.000   0.1972   0.01452   0.00467   0.0056   1.0000   1.0000
   2.250   0.2220   0.01462   0.00511   0.0062   1.0000   1.0000
   2.500   0.2471   0.01476   0.00569   0.0066   1.0000   1.0000
   2.750   0.3287   0.01714   0.00737  -0.0012   0.5596   1.0000
   3.000   0.3471   0.01870   0.00798   0.0019   0.4038   1.0000
   3.250   0.3725   0.02050   0.00922   0.0031   0.3035   1.0000
   3.500   0.3991   0.02234   0.01077   0.0041   0.2426   1.0000
   3.750   0.4255   0.02410   0.01252   0.0049   0.2018   1.0000
   4.000   0.4524   0.02606   0.01470   0.0057   0.1760   1.0000
   4.250   0.4785   0.02817   0.01691   0.0064   0.1581   1.0000
   4.500   0.5061   0.03099   0.02034   0.0070   0.1488   1.0000
   4.750   0.5313   0.03362   0.02333   0.0075   0.1372   1.0000
   5.000   0.5570   0.03729   0.02763   0.0077   0.1348   1.0000
   5.250   0.5815   0.04191   0.03291   0.0074   0.1376   1.0000
   5.500   0.6039   0.04664   0.03816   0.0068   0.1399   1.0000
   5.750   0.6243   0.05149   0.04337   0.0060   0.1412   1.0000
   6.000   0.6683   0.07610   0.06965  -0.0408   0.4005   1.0000
   6.250   0.6706   0.07918   0.07268  -0.0397   0.3682   1.0000
   6.750   0.6833   0.08609   0.07953  -0.0376   0.3180   1.0000
   7.000   0.6912   0.09002   0.08345  -0.0371   0.3021   1.0000
   7.500   0.6940   0.09731   0.09068  -0.0385   0.2748   1.0000
   7.750   0.6929   0.10089   0.09419  -0.0393   0.2638   1.0000
   8.000   0.7013   0.10529   0.09856  -0.0388   0.2542   1.0000
   8.250   0.7162   0.11028   0.10357  -0.0372   0.2416   1.0000
   8.500   0.7003   0.11196   0.10514  -0.0405   0.2329   1.0000
   8.750   0.7037   0.11596   0.10910  -0.0409   0.2240   1.0000
   9.000   0.7166   0.12087   0.11401  -0.0396   0.2124   1.0000
   9.250   0.7080   0.12302   0.11608  -0.0420   0.2039   1.0000
   9.500   0.7148   0.12755   0.12059  -0.0421   0.1970   1.0000
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