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HT12 (ht12-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HT12 (ht12-il)
Reynolds number: 100,000
Max Cl/Cd: 26.8 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht12-il-100000-n5.txt
Download as CSV file: xf-ht12-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT12                                            
  
 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  -0.7519   0.09840   0.09358   0.0363   1.0000   0.0271
  -8.500  -0.7534   0.09321   0.08844   0.0329   1.0000   0.0273
  -8.250  -0.7555   0.08766   0.08295   0.0286   1.0000   0.0273
  -8.000  -0.7550   0.08098   0.07628   0.0219   1.0000   0.0272
  -7.750  -0.7513   0.07294   0.06820   0.0139   1.0000   0.0269
  -7.500  -0.7459   0.06366   0.05875   0.0060   1.0000   0.0266
  -7.250  -0.7387   0.05460   0.04934   0.0002   1.0000   0.0262
  -7.000  -0.7280   0.04652   0.04071  -0.0036   1.0000   0.0260
  -6.750  -0.7122   0.04028   0.03384  -0.0055   1.0000   0.0261
  -6.500  -0.6925   0.03547   0.02838  -0.0063   1.0000   0.0267
  -6.250  -0.6701   0.03159   0.02389  -0.0066   1.0000   0.0276
  -6.000  -0.6458   0.02869   0.02042  -0.0065   1.0000   0.0297
  -5.750  -0.6198   0.02651   0.01758  -0.0062   1.0000   0.0322
  -5.500  -0.5950   0.02387   0.01471  -0.0060   1.0000   0.0341
  -5.250  -0.5692   0.02219   0.01285  -0.0057   1.0000   0.0364
  -5.000  -0.5428   0.02087   0.01131  -0.0054   1.0000   0.0406
  -4.750  -0.5166   0.01949   0.00977  -0.0050   1.0000   0.0453
  -4.500  -0.4905   0.01832   0.00851  -0.0047   1.0000   0.0502
  -4.250  -0.4641   0.01732   0.00743  -0.0044   1.0000   0.0587
  -4.000  -0.4374   0.01642   0.00647  -0.0041   1.0000   0.0696
  -3.750  -0.4108   0.01555   0.00566  -0.0039   1.0000   0.0873
  -3.500  -0.3840   0.01473   0.00491  -0.0038   1.0000   0.1155
  -3.250  -0.3574   0.01397   0.00437  -0.0037   1.0000   0.1647
  -3.000  -0.3310   0.01330   0.00398  -0.0035   1.0000   0.2309
  -2.750  -0.3045   0.01275   0.00368  -0.0033   1.0000   0.3014
  -2.500  -0.2782   0.01224   0.00342  -0.0030   1.0000   0.3697
  -2.250  -0.2521   0.01174   0.00314  -0.0026   1.0000   0.4411
  -2.000  -0.2267   0.01117   0.00292  -0.0019   1.0000   0.5275
  -1.750  -0.2043   0.01045   0.00277  -0.0002   1.0000   0.6648
  -1.500  -0.1785   0.00977   0.00270   0.0019   1.0000   0.8804
  -1.250  -0.1339   0.00958   0.00243  -0.0013   1.0000   1.0000
  -1.000  -0.1072   0.00954   0.00227  -0.0011   1.0000   1.0000
  -0.750  -0.0804   0.00951   0.00216  -0.0008   1.0000   1.0000
  -0.500  -0.0536   0.00949   0.00208  -0.0005   1.0000   1.0000
  -0.250  -0.0268   0.00948   0.00202  -0.0003   1.0000   1.0000
   0.000   0.0001   0.00948   0.00201   0.0000   1.0000   1.0000
   0.250   0.0269   0.00948   0.00202   0.0003   1.0000   1.0000
   0.500   0.0538   0.00949   0.00208   0.0005   1.0000   1.0000
   0.750   0.0806   0.00951   0.00216   0.0008   1.0000   1.0000
   1.000   0.1073   0.00954   0.00227   0.0011   1.0000   1.0000
   1.250   0.1341   0.00958   0.00243   0.0013   1.0000   1.0000
   1.500   0.1788   0.00977   0.00270  -0.0019   0.8785   1.0000
   1.750   0.2044   0.01045   0.00277   0.0002   0.6639   1.0000
   2.000   0.2269   0.01118   0.00292   0.0019   0.5269   1.0000
   2.250   0.2522   0.01175   0.00314   0.0026   0.4406   1.0000
   2.500   0.2783   0.01225   0.00342   0.0030   0.3693   1.0000
   2.750   0.3047   0.01275   0.00369   0.0033   0.3010   1.0000
   3.000   0.3312   0.01331   0.00399   0.0035   0.2304   1.0000
   3.250   0.3576   0.01398   0.00437   0.0037   0.1644   1.0000
   3.500   0.3842   0.01474   0.00491   0.0038   0.1153   1.0000
   3.750   0.4109   0.01556   0.00566   0.0039   0.0872   1.0000
   4.000   0.4375   0.01643   0.00647   0.0041   0.0695   1.0000
   4.250   0.4642   0.01732   0.00744   0.0044   0.0586   1.0000
   4.500   0.4907   0.01832   0.00852   0.0047   0.0502   1.0000
   4.750   0.5168   0.01949   0.00978   0.0050   0.0453   1.0000
   5.000   0.5430   0.02088   0.01132   0.0054   0.0405   1.0000
   5.250   0.5694   0.02220   0.01286   0.0057   0.0363   1.0000
   5.500   0.5953   0.02388   0.01472   0.0060   0.0340   1.0000
   5.750   0.6200   0.02654   0.01760   0.0062   0.0322   1.0000
   6.000   0.6460   0.02872   0.02045   0.0065   0.0297   1.0000
   6.250   0.6704   0.03162   0.02392   0.0065   0.0276   1.0000
   6.500   0.6927   0.03551   0.02844   0.0063   0.0267   1.0000
   6.750   0.7124   0.04035   0.03392   0.0054   0.0261   1.0000
   7.000   0.7282   0.04662   0.04082   0.0035   0.0260   1.0000
   7.250   0.7389   0.05472   0.04947  -0.0003   0.0262   1.0000
   7.500   0.7460   0.06383   0.05892  -0.0062   0.0266   1.0000
   7.750   0.7515   0.07311   0.06837  -0.0141   0.0270   1.0000
   8.000   0.7552   0.08111   0.07642  -0.0221   0.0272   1.0000
   8.250   0.7558   0.08777   0.08306  -0.0287   0.0274   1.0000
   8.500   0.7538   0.09334   0.08857  -0.0330   0.0274   1.0000
   8.750   0.7524   0.09852   0.09371  -0.0364   0.0272   1.0000
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