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HT08 (ht08-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HT08 (ht08-il)
Reynolds number: 1,000,000
Max Cl/Cd: 56.72 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ht08-il-1000000.txt
Download as CSV file: xf-ht08-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.8676   0.05232   0.05066   0.0018   1.0000   0.0075
  -8.500  -0.8843   0.03424   0.03170  -0.0037   1.0000   0.0073
  -8.250  -0.8824   0.02503   0.02155  -0.0042   1.0000   0.0074
  -8.000  -0.8650   0.02107   0.01708  -0.0039   1.0000   0.0077
  -7.750  -0.8421   0.01923   0.01500  -0.0037   1.0000   0.0080
  -7.500  -0.8176   0.01796   0.01356  -0.0035   1.0000   0.0082
  -7.250  -0.7925   0.01686   0.01230  -0.0032   1.0000   0.0086
  -7.000  -0.7668   0.01591   0.01121  -0.0030   1.0000   0.0090
  -6.750  -0.7406   0.01519   0.01037  -0.0028   1.0000   0.0096
  -6.500  -0.7142   0.01441   0.00947  -0.0026   1.0000   0.0102
  -6.250  -0.6874   0.01381   0.00876  -0.0024   1.0000   0.0106
  -6.000  -0.6621   0.01210   0.00681  -0.0021   1.0000   0.0113
  -5.750  -0.6356   0.01121   0.00584  -0.0019   1.0000   0.0123
  -5.500  -0.6084   0.01074   0.00533  -0.0018   1.0000   0.0131
  -5.250  -0.5810   0.01031   0.00484  -0.0017   1.0000   0.0142
  -5.000  -0.5534   0.01003   0.00453  -0.0016   1.0000   0.0153
  -4.750  -0.5261   0.00934   0.00374  -0.0015   1.0000   0.0170
  -4.500  -0.4985   0.00890   0.00328  -0.0014   1.0000   0.0194
  -4.250  -0.4706   0.00862   0.00297  -0.0013   1.0000   0.0215
  -4.000  -0.4428   0.00829   0.00260  -0.0013   1.0000   0.0242
  -3.750  -0.4149   0.00796   0.00229  -0.0012   1.0000   0.0302
  -3.500  -0.3869   0.00767   0.00201  -0.0012   1.0000   0.0379
  -3.250  -0.3589   0.00740   0.00178  -0.0011   1.0000   0.0505
  -3.000  -0.3310   0.00713   0.00160  -0.0011   1.0000   0.0703
  -2.750  -0.3031   0.00685   0.00144  -0.0012   1.0000   0.0983
  -2.500  -0.2752   0.00657   0.00131  -0.0012   1.0000   0.1337
  -2.250  -0.2473   0.00628   0.00118  -0.0012   1.0000   0.1782
  -2.000  -0.2194   0.00598   0.00108  -0.0013   1.0000   0.2309
  -1.750  -0.1915   0.00568   0.00099  -0.0014   1.0000   0.2911
  -1.500  -0.1637   0.00536   0.00092  -0.0014   1.0000   0.3626
  -1.250  -0.1361   0.00500   0.00086  -0.0015   1.0000   0.4466
  -1.000  -0.1088   0.00459   0.00081  -0.0015   1.0000   0.5536
  -0.750  -0.0820   0.00413   0.00079  -0.0013   1.0000   0.6765
  -0.500  -0.0568   0.00367   0.00079  -0.0006   1.0000   0.8012
  -0.250  -0.0361   0.00330   0.00082   0.0015   1.0000   0.9165
   0.000   0.0001   0.00320   0.00082   0.0000   0.9953   0.9953
   0.250   0.0362   0.00330   0.00082  -0.0015   0.9163   1.0000
   0.500   0.0569   0.00368   0.00079   0.0006   0.8004   1.0000
   0.750   0.0822   0.00413   0.00079   0.0013   0.6766   1.0000
   1.000   0.1089   0.00459   0.00081   0.0015   0.5531   1.0000
   1.250   0.1362   0.00500   0.00086   0.0015   0.4471   1.0000
   1.500   0.1639   0.00536   0.00092   0.0014   0.3621   1.0000
   1.750   0.1917   0.00568   0.00099   0.0014   0.2909   1.0000
   2.000   0.2195   0.00599   0.00108   0.0013   0.2295   1.0000
   2.250   0.2474   0.00628   0.00118   0.0012   0.1781   1.0000
   2.500   0.2753   0.00657   0.00131   0.0012   0.1336   1.0000
   2.750   0.3032   0.00685   0.00144   0.0011   0.0982   1.0000
   3.000   0.3312   0.00714   0.00160   0.0011   0.0701   1.0000
   3.250   0.3591   0.00740   0.00178   0.0011   0.0502   1.0000
   3.500   0.3871   0.00767   0.00201   0.0011   0.0378   1.0000
   3.750   0.4150   0.00796   0.00229   0.0012   0.0302   1.0000
   4.000   0.4429   0.00829   0.00260   0.0012   0.0242   1.0000
   4.250   0.4708   0.00862   0.00297   0.0013   0.0215   1.0000
   4.500   0.4986   0.00890   0.00328   0.0014   0.0193   1.0000
   4.750   0.5263   0.00935   0.00375   0.0015   0.0170   1.0000
   5.000   0.5536   0.01004   0.00454   0.0016   0.0153   1.0000
   5.250   0.5812   0.01032   0.00486   0.0017   0.0142   1.0000
   5.500   0.6086   0.01075   0.00534   0.0018   0.0131   1.0000
   5.750   0.6358   0.01121   0.00584   0.0019   0.0122   1.0000
   6.000   0.6624   0.01207   0.00679   0.0021   0.0113   1.0000
   6.250   0.6875   0.01383   0.00879   0.0024   0.0106   1.0000
   6.500   0.7144   0.01443   0.00949   0.0026   0.0102   1.0000
   6.750   0.7409   0.01517   0.01034   0.0028   0.0096   1.0000
   7.000   0.7671   0.01586   0.01116   0.0030   0.0090   1.0000
   7.250   0.7928   0.01685   0.01230   0.0032   0.0086   1.0000
   7.500   0.8180   0.01795   0.01355   0.0034   0.0082   1.0000
   7.750   0.8425   0.01918   0.01495   0.0036   0.0079   1.0000
   8.000   0.8653   0.02108   0.01709   0.0039   0.0077   1.0000
   8.250   0.8827   0.02506   0.02158   0.0042   0.0074   1.0000
   8.500   0.8822   0.03516   0.03269   0.0035   0.0073   1.0000
   9.250   0.6727   0.08183   0.08039  -0.0227   0.0114   1.0000
   9.500   0.6530   0.09077   0.08931  -0.0257   0.0116   1.0000
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