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HT05 (ht05-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HT05 (ht05-il)
Reynolds number: 200,000
Max Cl/Cd: 34.57 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht05-il-200000-n5.txt
Download as CSV file: xf-ht05-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT05                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.7447   0.09428   0.09080   0.0260   1.0000   0.0150
  -8.750  -0.7494   0.08864   0.08521   0.0224   1.0000   0.0149
  -8.500  -0.7559   0.08258   0.07919   0.0176   1.0000   0.0147
  -8.250  -0.7584   0.07508   0.07168   0.0108   1.0000   0.0145
  -8.000  -0.7589   0.06510   0.06162   0.0019   1.0000   0.0143
  -7.750  -0.7626   0.05111   0.04727  -0.0062   1.0000   0.0140
  -7.500  -0.7640   0.03920   0.03459  -0.0092   1.0000   0.0140
  -7.250  -0.7524   0.03315   0.02785  -0.0094   1.0000   0.0143
  -7.000  -0.7352   0.02900   0.02309  -0.0089   1.0000   0.0150
  -6.750  -0.7144   0.02615   0.01971  -0.0083   1.0000   0.0160
  -6.500  -0.6911   0.02435   0.01746  -0.0077   1.0000   0.0173
  -6.250  -0.6688   0.02180   0.01450  -0.0070   1.0000   0.0183
  -6.000  -0.6450   0.02012   0.01261  -0.0064   1.0000   0.0193
  -5.750  -0.6203   0.01892   0.01121  -0.0059   1.0000   0.0205
  -5.500  -0.5953   0.01779   0.00991  -0.0053   1.0000   0.0221
  -5.250  -0.5697   0.01699   0.00894  -0.0048   1.0000   0.0245
  -5.000  -0.5447   0.01588   0.00772  -0.0042   1.0000   0.0269
  -4.750  -0.5194   0.01503   0.00680  -0.0037   1.0000   0.0296
  -4.500  -0.4937   0.01436   0.00602  -0.0032   1.0000   0.0330
  -4.250  -0.4679   0.01372   0.00532  -0.0028   1.0000   0.0383
  -4.000  -0.4420   0.01318   0.00475  -0.0023   1.0000   0.0449
  -3.750  -0.4160   0.01264   0.00420  -0.0019   1.0000   0.0541
  -3.500  -0.3900   0.01217   0.00375  -0.0015   1.0000   0.0689
  -3.250  -0.3640   0.01175   0.00337  -0.0010   1.0000   0.0879
  -3.000  -0.3381   0.01133   0.00308  -0.0007   1.0000   0.1176
  -2.750  -0.3122   0.01096   0.00284  -0.0003   1.0000   0.1510
  -2.500  -0.2863   0.01060   0.00263   0.0001   1.0000   0.1904
  -2.250  -0.2605   0.01024   0.00243   0.0005   1.0000   0.2346
  -2.000  -0.2350   0.00987   0.00227   0.0010   1.0000   0.2874
  -1.750  -0.2098   0.00945   0.00214   0.0015   1.0000   0.3594
  -1.500  -0.1854   0.00896   0.00209   0.0021   1.0000   0.4647
  -1.250  -0.1610   0.00863   0.00208   0.0030   1.0000   0.5628
  -1.000  -0.1350   0.00851   0.00202   0.0036   1.0000   0.6137
  -0.750  -0.1095   0.00827   0.00188   0.0042   1.0000   0.6421
  -0.500  -0.0878   0.00761   0.00181   0.0059   1.0000   0.7156
  -0.250  -0.0330   0.00738   0.00203   0.0011   1.0000   0.9869
   0.000   0.0001   0.00739   0.00203   0.0000   1.0000   1.0000
   0.250   0.0332   0.00738   0.00203  -0.0011   0.9868   1.0000
   0.500   0.0878   0.00762   0.00180  -0.0059   0.7120   1.0000
   0.750   0.1096   0.00827   0.00188  -0.0042   0.6419   1.0000
   1.000   0.1352   0.00851   0.00202  -0.0036   0.6135   1.0000
   1.250   0.1611   0.00863   0.00208  -0.0030   0.5622   1.0000
   1.500   0.1856   0.00896   0.00209  -0.0021   0.4640   1.0000
   1.750   0.2099   0.00945   0.00214  -0.0015   0.3592   1.0000
   2.000   0.2351   0.00987   0.00227  -0.0010   0.2874   1.0000
   2.250   0.2607   0.01024   0.00243  -0.0005   0.2345   1.0000
   2.500   0.2864   0.01060   0.00263  -0.0001   0.1900   1.0000
   2.750   0.3123   0.01096   0.00284   0.0003   0.1508   1.0000
   3.000   0.3382   0.01133   0.00308   0.0007   0.1175   1.0000
   3.250   0.3641   0.01175   0.00337   0.0010   0.0879   1.0000
   3.500   0.3902   0.01217   0.00375   0.0015   0.0688   1.0000
   3.750   0.4162   0.01264   0.00421   0.0019   0.0539   1.0000
   4.000   0.4421   0.01318   0.00475   0.0023   0.0449   1.0000
   4.250   0.4681   0.01373   0.00533   0.0028   0.0382   1.0000
   4.500   0.4938   0.01436   0.00602   0.0032   0.0329   1.0000
   4.750   0.5196   0.01503   0.00680   0.0037   0.0295   1.0000
   5.000   0.5448   0.01591   0.00774   0.0042   0.0269   1.0000
   5.250   0.5699   0.01698   0.00894   0.0048   0.0245   1.0000
   5.500   0.5954   0.01780   0.00992   0.0053   0.0221   1.0000
   5.750   0.6205   0.01892   0.01121   0.0059   0.0205   1.0000
   6.000   0.6452   0.02013   0.01261   0.0064   0.0193   1.0000
   6.250   0.6688   0.02187   0.01457   0.0070   0.0183   1.0000
   6.500   0.6913   0.02433   0.01745   0.0077   0.0173   1.0000
   6.750   0.7146   0.02615   0.01971   0.0083   0.0159   1.0000
   7.000   0.7353   0.02905   0.02314   0.0089   0.0150   1.0000
   7.250   0.7525   0.03317   0.02788   0.0094   0.0144   1.0000
   7.500   0.7643   0.03918   0.03457   0.0092   0.0140   1.0000
   7.750   0.7628   0.05111   0.04727   0.0062   0.0140   1.0000
   8.000   0.7590   0.06520   0.06172  -0.0020   0.0143   1.0000
   8.250   0.7586   0.07519   0.07179  -0.0109   0.0146   1.0000
   8.500   0.7561   0.08268   0.07929  -0.0178   0.0148   1.0000
   8.750   0.7496   0.08876   0.08533  -0.0226   0.0149   1.0000
   9.000   0.7451   0.09440   0.09092  -0.0262   0.0151   1.0000
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