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HT23 (ht23-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HT23 (ht23-il)
Reynolds number: 100,000
Max Cl/Cd: 37.2 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ht23-il-100000.txt
Download as CSV file: xf-ht23-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT23                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6420   0.10367   0.09897   0.0315   1.0000   0.0872
  -8.000  -0.6431   0.09985   0.09520   0.0275   1.0000   0.0907
  -7.750  -0.6532   0.09485   0.09023   0.0108   1.0000   0.0931
  -7.500  -0.6441   0.08973   0.08519   0.0145   1.0000   0.0949
  -7.250  -0.6316   0.08670   0.08218   0.0185   1.0000   0.0984
  -7.000  -0.6233   0.08216   0.07760   0.0132   1.0000   0.1040
  -6.750  -0.6165   0.07569   0.07106   0.0035   1.0000   0.1090
  -6.500  -0.6028   0.07302   0.06844   0.0068   1.0000   0.1148
  -6.250  -0.5907   0.06745   0.06273   0.0000   1.0000   0.1240
  -6.000  -0.5755   0.06314   0.05822  -0.0046   1.0000   0.1369
  -5.750  -0.5596   0.06019   0.05540  -0.0019   1.0000   0.1438
  -5.500  -0.5423   0.05605   0.05115  -0.0042   1.0000   0.1556
  -5.250  -0.5235   0.05234   0.04735  -0.0057   1.0000   0.1699
  -5.000  -0.5037   0.04894   0.04386  -0.0067   1.0000   0.1858
  -4.750  -0.4552   0.03475   0.02782  -0.0150   1.0000   0.0833
  -4.500  -0.4234   0.02976   0.02177  -0.0144   1.0000   0.0649
  -4.250  -0.3966   0.02647   0.01808  -0.0141   1.0000   0.0630
  -4.000  -0.3683   0.02435   0.01546  -0.0136   1.0000   0.0650
  -3.750  -0.3397   0.02243   0.01312  -0.0130   1.0000   0.0664
  -3.500  -0.3125   0.01988   0.01049  -0.0125   1.0000   0.0688
  -3.250  -0.2850   0.01844   0.00900  -0.0120   1.0000   0.0755
  -3.000  -0.2581   0.01695   0.00753  -0.0114   1.0000   0.0856
  -2.750  -0.2315   0.01565   0.00633  -0.0107   1.0000   0.1041
  -2.500  -0.2058   0.01407   0.00514  -0.0101   1.0000   0.1573
  -2.250  -0.1905   0.01093   0.00448  -0.0076   1.0000   0.6302
  -2.000  -0.1376   0.01003   0.00414  -0.0096   1.0000   1.0000
  -1.750  -0.1120   0.00995   0.00379  -0.0092   1.0000   1.0000
  -1.500  -0.0863   0.00989   0.00351  -0.0088   1.0000   1.0000
  -1.250  -0.0604   0.00984   0.00329  -0.0084   1.0000   1.0000
  -1.000  -0.0344   0.00981   0.00311  -0.0081   1.0000   1.0000
  -0.750  -0.0084   0.00979   0.00298  -0.0077   1.0000   1.0000
  -0.500   0.0176   0.00979   0.00289  -0.0074   1.0000   1.0000
  -0.250   0.0436   0.00980   0.00284  -0.0071   1.0000   1.0000
   0.000   0.0696   0.00982   0.00284  -0.0068   1.0000   1.0000
   0.250   0.0954   0.00986   0.00288  -0.0065   1.0000   1.0000
   0.500   0.1210   0.00992   0.00299  -0.0064   1.0000   1.0000
   0.750   0.1459   0.01003   0.00319  -0.0064   1.0000   1.0000
   1.000   0.2134   0.01021   0.00337  -0.0142   0.9008   1.0000
   1.250   0.2426   0.01057   0.00340  -0.0128   0.7903   1.0000
   1.500   0.2643   0.01104   0.00350  -0.0105   0.7162   1.0000
   1.750   0.2877   0.01152   0.00365  -0.0089   0.6622   1.0000
   2.000   0.3125   0.01199   0.00385  -0.0079   0.6183   1.0000
   2.250   0.3382   0.01243   0.00409  -0.0071   0.5798   1.0000
   2.500   0.3640   0.01287   0.00437  -0.0064   0.5470   1.0000
   2.750   0.3901   0.01331   0.00464  -0.0058   0.5167   1.0000
   3.000   0.4164   0.01373   0.00495  -0.0053   0.4880   1.0000
   3.250   0.4429   0.01415   0.00528  -0.0049   0.4604   1.0000
   3.500   0.4694   0.01458   0.00566  -0.0044   0.4337   1.0000
   3.750   0.4958   0.01502   0.00603  -0.0040   0.4079   1.0000
   4.000   0.5221   0.01547   0.00638  -0.0035   0.3830   1.0000
   4.250   0.5485   0.01590   0.00677  -0.0031   0.3567   1.0000
   4.500   0.5748   0.01632   0.00721  -0.0027   0.3298   1.0000
   4.750   0.6010   0.01675   0.00761  -0.0023   0.3022   1.0000
   5.000   0.6270   0.01719   0.00802  -0.0019   0.2736   1.0000
   5.250   0.6527   0.01766   0.00846  -0.0016   0.2435   1.0000
   5.500   0.6781   0.01823   0.00892  -0.0012   0.2122   1.0000
   5.750   0.7035   0.01900   0.00966  -0.0009   0.1789   1.0000
   6.000   0.7286   0.02009   0.01068  -0.0004   0.1503   1.0000
   6.250   0.7532   0.02129   0.01174  -0.0001   0.1285   1.0000
   6.500   0.7782   0.02287   0.01329   0.0004   0.1140   1.0000
   6.750   0.8033   0.02423   0.01476   0.0009   0.1023   1.0000
   7.000   0.8284   0.02598   0.01681   0.0014   0.0938   1.0000
   7.250   0.8524   0.02834   0.01910   0.0017   0.0881   1.0000
   7.500   0.8763   0.03026   0.02164   0.0023   0.0824   1.0000
   7.750   0.8993   0.03228   0.02382   0.0027   0.0777   1.0000
   8.000   0.9193   0.03610   0.02789   0.0030   0.0753   1.0000
   8.250   0.9365   0.03978   0.03236   0.0034   0.0738   1.0000
   8.500   0.9489   0.04423   0.03754   0.0034   0.0716   1.0000
   8.750   0.9556   0.04967   0.04360   0.0028   0.0705   1.0000
   9.000   0.9533   0.05666   0.05114   0.0012   0.0715   1.0000
   9.250   0.9453   0.06394   0.05878  -0.0014   0.0728   1.0000
   9.500   0.9367   0.07074   0.06577  -0.0042   0.0742   1.0000
   9.750   0.9331   0.07691   0.07206  -0.0065   0.0763   1.0000
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