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HT08 (ht08-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HT08 (ht08-il)
Reynolds number: 100,000
Max Cl/Cd: 26.08 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht08-il-100000-n5.txt
Download as CSV file: xf-ht08-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.7415   0.09735   0.09251   0.0306   1.0000   0.0270
  -8.500  -0.7433   0.09212   0.08732   0.0271   1.0000   0.0271
  -8.250  -0.7462   0.08646   0.08172   0.0224   1.0000   0.0270
  -8.000  -0.7454   0.07968   0.07493   0.0157   1.0000   0.0268
  -7.750  -0.7423   0.07218   0.06736   0.0089   1.0000   0.0266
  -7.500  -0.7373   0.06428   0.05929   0.0031   1.0000   0.0264
  -7.250  -0.7300   0.05651   0.05123  -0.0012   1.0000   0.0262
  -7.000  -0.7200   0.04898   0.04325  -0.0041   1.0000   0.0259
  -6.750  -0.7060   0.04253   0.03621  -0.0057   1.0000   0.0258
  -6.500  -0.6879   0.03733   0.03039  -0.0064   1.0000   0.0262
  -6.250  -0.6669   0.03313   0.02556  -0.0066   1.0000   0.0269
  -6.000  -0.6435   0.02987   0.02172  -0.0064   1.0000   0.0285
  -5.750  -0.6182   0.02743   0.01861  -0.0061   1.0000   0.0313
  -5.500  -0.5931   0.02476   0.01552  -0.0058   1.0000   0.0328
  -5.250  -0.5677   0.02284   0.01343  -0.0055   1.0000   0.0349
  -5.000  -0.5416   0.02142   0.01182  -0.0051   1.0000   0.0383
  -4.750  -0.5148   0.02028   0.01039  -0.0047   1.0000   0.0431
  -4.500  -0.4895   0.01876   0.00885  -0.0043   1.0000   0.0474
  -4.250  -0.4631   0.01780   0.00775  -0.0039   1.0000   0.0545
  -4.000  -0.4370   0.01683   0.00679  -0.0037   1.0000   0.0644
  -3.750  -0.4106   0.01594   0.00588  -0.0034   1.0000   0.0779
  -3.500  -0.3842   0.01512   0.00516  -0.0032   1.0000   0.1014
  -3.250  -0.3579   0.01434   0.00452  -0.0030   1.0000   0.1407
  -3.000  -0.3317   0.01360   0.00405  -0.0028   1.0000   0.2024
  -2.750  -0.3058   0.01288   0.00369  -0.0026   1.0000   0.2877
  -2.500  -0.2804   0.01214   0.00339  -0.0023   1.0000   0.3949
  -2.250  -0.2565   0.01134   0.00314  -0.0014   1.0000   0.5335
  -2.000  -0.2360   0.01054   0.00302   0.0009   1.0000   0.7051
  -1.750  -0.2068   0.01003   0.00294   0.0023   1.0000   0.8919
  -1.500  -0.1559   0.00986   0.00266  -0.0022   1.0000   1.0000
  -1.250  -0.1301   0.00981   0.00247  -0.0018   1.0000   1.0000
  -1.000  -0.1042   0.00976   0.00232  -0.0014   1.0000   1.0000
  -0.750  -0.0782   0.00973   0.00220  -0.0011   1.0000   1.0000
  -0.500  -0.0522   0.00970   0.00213  -0.0007   1.0000   1.0000
  -0.250  -0.0261   0.00969   0.00207  -0.0004   1.0000   1.0000
   0.000   0.0001   0.00968   0.00205   0.0000   1.0000   1.0000
   0.250   0.0262   0.00969   0.00207   0.0004   1.0000   1.0000
   0.500   0.0523   0.00970   0.00213   0.0007   1.0000   1.0000
   0.750   0.0784   0.00973   0.00220   0.0011   1.0000   1.0000
   1.000   0.1044   0.00976   0.00232   0.0014   1.0000   1.0000
   1.250   0.1302   0.00981   0.00247   0.0018   1.0000   1.0000
   1.500   0.1560   0.00986   0.00268   0.0022   1.0000   1.0000
   1.750   0.2070   0.01003   0.00294  -0.0023   0.8911   1.0000
   2.000   0.2361   0.01054   0.00302  -0.0009   0.7044   1.0000
   2.250   0.2566   0.01134   0.00314   0.0014   0.5329   1.0000
   2.500   0.2805   0.01214   0.00339   0.0023   0.3944   1.0000
   2.750   0.3060   0.01288   0.00369   0.0026   0.2873   1.0000
   3.000   0.3318   0.01361   0.00406   0.0028   0.2021   1.0000
   3.250   0.3580   0.01435   0.00452   0.0030   0.1404   1.0000
   3.500   0.3844   0.01512   0.00516   0.0032   0.1013   1.0000
   3.750   0.4108   0.01594   0.00588   0.0034   0.0778   1.0000
   4.000   0.4372   0.01683   0.00679   0.0037   0.0644   1.0000
   4.250   0.4632   0.01781   0.00776   0.0039   0.0545   1.0000
   4.500   0.4896   0.01877   0.00886   0.0043   0.0473   1.0000
   4.750   0.5150   0.02029   0.01039   0.0047   0.0431   1.0000
   5.000   0.5418   0.02142   0.01182   0.0051   0.0382   1.0000
   5.250   0.5679   0.02285   0.01344   0.0055   0.0349   1.0000
   5.500   0.5932   0.02477   0.01554   0.0057   0.0328   1.0000
   5.750   0.6184   0.02744   0.01862   0.0061   0.0312   1.0000
   6.000   0.6437   0.02989   0.02173   0.0064   0.0285   1.0000
   6.250   0.6671   0.03315   0.02559   0.0065   0.0269   1.0000
   6.500   0.6881   0.03736   0.03042   0.0064   0.0262   1.0000
   6.750   0.7062   0.04257   0.03626   0.0057   0.0258   1.0000
   7.000   0.7202   0.04903   0.04330   0.0041   0.0259   1.0000
   7.250   0.7302   0.05657   0.05129   0.0011   0.0262   1.0000
   7.500   0.7375   0.06436   0.05937  -0.0032   0.0264   1.0000
   7.750   0.7425   0.07226   0.06744  -0.0090   0.0266   1.0000
   8.000   0.7457   0.07976   0.07502  -0.0158   0.0268   1.0000
   8.250   0.7466   0.08653   0.08179  -0.0226   0.0270   1.0000
   8.500   0.7438   0.09219   0.08740  -0.0272   0.0271   1.0000
   8.750   0.7420   0.09742   0.09258  -0.0308   0.0270   1.0000
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