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HT08 (ht08-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HT08 (ht08-il)
Reynolds number: 50,000
Max Cl/Cd: 20.07 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht08-il-50000-n5.txt
Download as CSV file: xf-ht08-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.7287   0.10270   0.09583   0.0291   1.0000   0.0495
  -8.500  -0.7295   0.09769   0.09088   0.0258   1.0000   0.0492
  -8.250  -0.7309   0.09242   0.08567   0.0218   1.0000   0.0488
  -8.000  -0.7297   0.08650   0.07976   0.0165   1.0000   0.0485
  -7.750  -0.7268   0.08024   0.07347   0.0112   1.0000   0.0483
  -7.500  -0.7222   0.07396   0.06709   0.0066   1.0000   0.0482
  -7.250  -0.7157   0.06772   0.06067   0.0025   1.0000   0.0483
  -7.000  -0.7067   0.06156   0.05424  -0.0009   1.0000   0.0482
  -6.750  -0.6949   0.05550   0.04778  -0.0036   1.0000   0.0480
  -6.500  -0.6796   0.04992   0.04172  -0.0054   1.0000   0.0480
  -6.250  -0.6613   0.04490   0.03610  -0.0066   1.0000   0.0485
  -6.000  -0.6402   0.04051   0.03109  -0.0072   1.0000   0.0497
  -5.750  -0.6168   0.03678   0.02662  -0.0074   1.0000   0.0535
  -5.500  -0.5923   0.03351   0.02278  -0.0074   1.0000   0.0569
  -5.250  -0.5672   0.03094   0.01990  -0.0071   1.0000   0.0598
  -5.000  -0.5409   0.02864   0.01720  -0.0067   1.0000   0.0647
  -4.750  -0.5149   0.02678   0.01511  -0.0063   1.0000   0.0727
  -4.500  -0.4881   0.02497   0.01293  -0.0056   1.0000   0.0802
  -4.250  -0.4621   0.02352   0.01139  -0.0051   1.0000   0.0928
  -4.000  -0.4355   0.02212   0.00990  -0.0046   1.0000   0.1089
  -3.750  -0.4089   0.02087   0.00868  -0.0043   1.0000   0.1361
  -3.500  -0.3829   0.01959   0.00753  -0.0041   1.0000   0.1785
  -3.250  -0.3576   0.01831   0.00667  -0.0039   1.0000   0.2550
  -3.000  -0.3339   0.01704   0.00602  -0.0033   1.0000   0.3778
  -2.750  -0.3141   0.01575   0.00558  -0.0013   1.0000   0.5481
  -2.500  -0.2946   0.01467   0.00538   0.0027   1.0000   0.7782
  -2.250  -0.2284   0.01422   0.00471  -0.0035   1.0000   1.0000
  -2.000  -0.2037   0.01409   0.00427  -0.0031   1.0000   1.0000
  -1.750  -0.1787   0.01397   0.00390  -0.0027   1.0000   1.0000
  -1.500  -0.1535   0.01389   0.00358  -0.0023   1.0000   1.0000
  -1.250  -0.1281   0.01381   0.00333  -0.0019   1.0000   1.0000
  -1.000  -0.1026   0.01376   0.00313  -0.0015   1.0000   1.0000
  -0.750  -0.0770   0.01371   0.00298  -0.0011   1.0000   1.0000
  -0.500  -0.0514   0.01368   0.00288  -0.0008   1.0000   1.0000
  -0.250  -0.0257   0.01366   0.00281  -0.0004   1.0000   1.0000
   0.000   0.0001   0.01366   0.00278   0.0000   1.0000   1.0000
   0.250   0.0258   0.01366   0.00281   0.0004   1.0000   1.0000
   0.500   0.0515   0.01368   0.00288   0.0008   1.0000   1.0000
   0.750   0.0772   0.01371   0.00298   0.0011   1.0000   1.0000
   1.000   0.1028   0.01376   0.00313   0.0015   1.0000   1.0000
   1.250   0.1282   0.01381   0.00333   0.0019   1.0000   1.0000
   1.500   0.1536   0.01389   0.00358   0.0023   1.0000   1.0000
   1.750   0.1788   0.01398   0.00391   0.0027   1.0000   1.0000
   2.000   0.2038   0.01409   0.00427   0.0031   1.0000   1.0000
   2.250   0.2286   0.01422   0.00471   0.0035   1.0000   1.0000
   2.500   0.2947   0.01468   0.00538  -0.0027   0.7768   1.0000
   2.750   0.3142   0.01576   0.00558   0.0013   0.5471   1.0000
   3.000   0.3340   0.01705   0.00602   0.0033   0.3772   1.0000
   3.250   0.3577   0.01831   0.00667   0.0039   0.2546   1.0000
   3.500   0.3830   0.01959   0.00753   0.0041   0.1782   1.0000
   3.750   0.4091   0.02088   0.00867   0.0043   0.1359   1.0000
   4.000   0.4357   0.02213   0.00991   0.0046   0.1089   1.0000
   4.250   0.4622   0.02352   0.01140   0.0051   0.0927   1.0000
   4.500   0.4882   0.02498   0.01294   0.0056   0.0802   1.0000
   4.750   0.5151   0.02679   0.01512   0.0063   0.0727   1.0000
   5.000   0.5410   0.02866   0.01721   0.0067   0.0647   1.0000
   5.250   0.5674   0.03095   0.01992   0.0071   0.0598   1.0000
   5.500   0.5925   0.03352   0.02280   0.0074   0.0568   1.0000
   5.750   0.6170   0.03680   0.02665   0.0074   0.0535   1.0000
   6.000   0.6404   0.04053   0.03112   0.0071   0.0497   1.0000
   6.250   0.6615   0.04493   0.03613   0.0065   0.0485   1.0000
   6.500   0.6798   0.04995   0.04176   0.0054   0.0480   1.0000
   6.750   0.6951   0.05554   0.04782   0.0035   0.0480   1.0000
   7.000   0.7069   0.06160   0.05428   0.0008   0.0482   1.0000
   7.250   0.7159   0.06777   0.06072  -0.0026   0.0483   1.0000
   7.500   0.7225   0.07401   0.06714  -0.0066   0.0482   1.0000
   7.750   0.7271   0.08030   0.07352  -0.0113   0.0483   1.0000
   8.000   0.7301   0.08655   0.07981  -0.0166   0.0485   1.0000
   8.250   0.7313   0.09248   0.08573  -0.0219   0.0488   1.0000
   8.500   0.7299   0.09775   0.09093  -0.0260   0.0491   1.0000
   8.750   0.7292   0.10276   0.09590  -0.0292   0.0495   1.0000
   9.000   0.7291   0.10763   0.10072  -0.0320   0.0501   1.0000
   9.250   0.7297   0.11240   0.10544  -0.0343   0.0511   1.0000
   9.500   0.7318   0.11701   0.11002  -0.0361   0.0525   1.0000
   9.750   0.7374   0.12138   0.11439  -0.0364   0.0543   1.0000
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