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HT22 (ht22-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HT22 (ht22-il)
Reynolds number: 50,000
Max Cl/Cd: 27.25 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht22-il-50000-n5.txt
Download as CSV file: xf-ht22-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT22                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6736   0.13300   0.12604   0.0417   1.0001   0.0876
  -9.500  -0.6788   0.13066   0.12377   0.0372   1.0001   0.0887
  -9.250  -0.6827   0.12791   0.12109   0.0329   1.0001   0.0891
  -9.000  -0.6576   0.12087   0.11397   0.0389   1.0001   0.0951
  -8.750  -0.6554   0.11748   0.11063   0.0369   1.0001   0.0995
  -8.500  -0.6621   0.11495   0.10820   0.0315   1.0001   0.1025
  -8.250  -0.6677   0.11198   0.10535   0.0247   1.0001   0.1032
  -8.000  -0.6460   0.10599   0.09931   0.0315   1.0001   0.1079
  -7.750  -0.6415   0.10228   0.09564   0.0297   1.0001   0.1114
  -7.500  -0.6459   0.09898   0.09240   0.0178   1.0001   0.1172
  -7.000  -0.6248   0.08951   0.08300   0.0179   1.0001   0.1207
  -6.750  -0.6139   0.08517   0.07865   0.0156   1.0001   0.1227
  -6.500  -0.5896   0.07446   0.06762   0.0037   1.0001   0.0581
  -6.000  -0.5517   0.06161   0.05415  -0.0071   1.0001   0.0480
  -5.750  -0.5342   0.05712   0.04954  -0.0086   1.0001   0.0471
  -5.500  -0.5139   0.05251   0.04466  -0.0106   1.0001   0.0466
  -5.250  -0.4907   0.04791   0.03961  -0.0126   1.0001   0.0472
  -5.000  -0.4654   0.04371   0.03478  -0.0142   1.0001   0.0483
  -4.750  -0.4410   0.03982   0.03046  -0.0150   1.0001   0.0490
  -4.500  -0.4154   0.03631   0.02648  -0.0154   1.0001   0.0493
  -4.250  -0.3893   0.03320   0.02297  -0.0156   1.0001   0.0501
  -4.000  -0.3632   0.03077   0.02028  -0.0156   1.0001   0.0525
  -3.750  -0.3358   0.02867   0.01779  -0.0155   1.0001   0.0571
  -3.500  -0.3072   0.02649   0.01511  -0.0150   1.0001   0.0601
  -3.250  -0.2796   0.02448   0.01281  -0.0145   1.0001   0.0634
  -3.000  -0.2527   0.02307   0.01129  -0.0140   1.0001   0.0715
  -2.750  -0.2252   0.02156   0.00962  -0.0133   1.0001   0.0778
  -2.500  -0.1981   0.02043   0.00836  -0.0127   1.0001   0.0904
  -2.250  -0.1711   0.01928   0.00718  -0.0122   1.0001   0.1055
  -2.000  -0.1442   0.01816   0.00617  -0.0119   1.0001   0.1372
  -1.750  -0.1184   0.01637   0.00525  -0.0119   1.0001   0.2686
  -1.500  -0.0847   0.01362   0.00469  -0.0110   1.0001   0.9999
  -1.250  -0.0583   0.01356   0.00426  -0.0105   1.0001   0.9999
  -1.000  -0.0320   0.01353   0.00392  -0.0101   1.0001   0.9999
  -0.750  -0.0057   0.01350   0.00368  -0.0098   1.0001   0.9999
  -0.500   0.0205   0.01349   0.00351  -0.0094   1.0001   0.9999
  -0.250   0.0467   0.01349   0.00337  -0.0091   1.0001   0.9999
   0.000   0.0728   0.01351   0.00330  -0.0087   1.0001   0.9999
   0.250   0.0988   0.01353   0.00328  -0.0084   1.0001   0.9999
   0.500   0.1248   0.01357   0.00332  -0.0081   1.0001   0.9999
   0.750   0.1505   0.01363   0.00340  -0.0078   1.0001   0.9999
   1.000   0.1761   0.01371   0.00354  -0.0075   1.0001   0.9999
   1.250   0.2015   0.01381   0.00374  -0.0073   1.0001   0.9999
   1.500   0.2354   0.01397   0.00405  -0.0089   0.9740   0.9999
   1.750   0.2896   0.01427   0.00439  -0.0136   0.8561   0.9999
   2.000   0.3223   0.01471   0.00458  -0.0130   0.7457   0.9999
   2.250   0.3451   0.01526   0.00478  -0.0108   0.6628   0.9999
   2.500   0.3679   0.01585   0.00504  -0.0090   0.5970   0.9999
   2.750   0.3917   0.01643   0.00540  -0.0077   0.5412   0.9999
   3.000   0.4162   0.01701   0.00577  -0.0066   0.4920   0.9999
   3.250   0.4412   0.01757   0.00619  -0.0058   0.4453   0.9999
   3.500   0.4663   0.01815   0.00664  -0.0051   0.4000   0.9999
   3.750   0.4916   0.01873   0.00716  -0.0045   0.3545   0.9999
   4.000   0.5169   0.01935   0.00767  -0.0040   0.3085   0.9999
   4.250   0.5422   0.02003   0.00822  -0.0036   0.2631   0.9999
   4.500   0.5678   0.02084   0.00891  -0.0033   0.2199   0.9999
   4.750   0.5938   0.02181   0.00985  -0.0031   0.1827   0.9999
   5.000   0.6192   0.02291   0.01089  -0.0028   0.1544   0.9999
   5.250   0.6444   0.02412   0.01208  -0.0025   0.1336   0.9999
   5.500   0.6695   0.02541   0.01345  -0.0021   0.1171   0.9999
   5.750   0.6943   0.02691   0.01507  -0.0015   0.1064   0.9999
   6.000   0.7184   0.02832   0.01650  -0.0012   0.0959   0.9999
   6.250   0.7435   0.03013   0.01870  -0.0007   0.0882   0.9999
   6.500   0.7672   0.03205   0.02065  -0.0003   0.0834   0.9999
   6.750   0.7912   0.03445   0.02364   0.0000   0.0773   0.9999
   7.000   0.8136   0.03637   0.02578   0.0002   0.0719   0.9999
   7.250   0.8348   0.03945   0.02923   0.0004   0.0694   0.9999
   7.500   0.8534   0.04363   0.03417   0.0002   0.0674   0.9999
   7.750   0.8683   0.04823   0.03945  -0.0005   0.0649   0.9999
   8.000   0.8815   0.05225   0.04391  -0.0013   0.0619   0.9999
   8.250   0.8964   0.05497   0.04675  -0.0015   0.0591   0.9999
   8.500   0.9055   0.05941   0.05140  -0.0023   0.0579   0.9999
   8.750   0.9039   0.06593   0.05840  -0.0051   0.0577   0.9999
   9.000   0.8976   0.07271   0.06548  -0.0088   0.0577   0.9999
   9.250   0.8886   0.07963   0.07257  -0.0133   0.0579   0.9999
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