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HT08 (ht08-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HT08 (ht08-il)
Reynolds number: 200,000
Max Cl/Cd: 33.1 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ht08-il-200000.txt
Download as CSV file: xf-ht08-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7468   0.11544   0.11203   0.0334   1.0000   0.0430
  -9.250  -0.7467   0.11058   0.10719   0.0296   1.0000   0.0431
  -9.000  -0.7525   0.10346   0.10013   0.0286   1.0000   0.0438
  -8.750  -0.7458   0.10015   0.09680   0.0313   1.0000   0.0449
  -8.500  -0.7411   0.09668   0.09334   0.0311   1.0000   0.0460
  -8.250  -0.7389   0.09274   0.08942   0.0293   1.0000   0.0471
  -8.000  -0.7383   0.08828   0.08499   0.0260   1.0000   0.0482
  -7.750  -0.7344   0.08284   0.07955   0.0203   1.0000   0.0497
  -7.500  -0.7280   0.07642   0.07308   0.0131   1.0000   0.0517
  -7.250  -0.7179   0.06734   0.06343  -0.0009   1.0000   0.0553
  -7.000  -0.7137   0.05912   0.05517  -0.0029   1.0000   0.0566
  -6.750  -0.6991   0.05587   0.05195  -0.0025   1.0000   0.0581
  -6.500  -0.6829   0.05245   0.04845  -0.0031   1.0000   0.0605
  -6.250  -0.6658   0.04638   0.04153  -0.0065   1.0000   0.0692
  -6.000  -0.6449   0.03439   0.02884  -0.0065   1.0000   0.0410
  -5.750  -0.6229   0.02951   0.02340  -0.0065   1.0000   0.0396
  -5.500  -0.5984   0.02482   0.01804  -0.0060   1.0000   0.0375
  -5.250  -0.5720   0.02183   0.01452  -0.0055   1.0000   0.0378
  -5.000  -0.5451   0.01982   0.01215  -0.0050   1.0000   0.0397
  -4.750  -0.5173   0.01900   0.01103  -0.0045   1.0000   0.0430
  -4.500  -0.4914   0.01641   0.00828  -0.0041   1.0000   0.0463
  -4.250  -0.4645   0.01533   0.00715  -0.0037   1.0000   0.0512
  -4.000  -0.4379   0.01420   0.00598  -0.0034   1.0000   0.0588
  -3.750  -0.4107   0.01342   0.00514  -0.0030   1.0000   0.0681
  -3.500  -0.3842   0.01240   0.00425  -0.0028   1.0000   0.0864
  -3.250  -0.3572   0.01155   0.00352  -0.0026   1.0000   0.1220
  -3.000  -0.3308   0.01060   0.00303  -0.0027   1.0000   0.2024
  -2.750  -0.3047   0.00979   0.00272  -0.0026   1.0000   0.3181
  -2.500  -0.2795   0.00896   0.00249  -0.0024   1.0000   0.4601
  -2.250  -0.2574   0.00801   0.00233  -0.0010   1.0000   0.6456
  -2.000  -0.2409   0.00728   0.00231   0.0027   1.0000   0.8419
  -1.750  -0.1841   0.00710   0.00219  -0.0024   1.0000   0.9998
  -1.500  -0.1580   0.00704   0.00201  -0.0020   1.0000   1.0000
  -1.250  -0.1319   0.00699   0.00185  -0.0017   1.0000   1.0000
  -1.000  -0.1057   0.00696   0.00173  -0.0013   1.0000   1.0000
  -0.750  -0.0793   0.00693   0.00165  -0.0010   1.0000   1.0000
  -0.500  -0.0529   0.00691   0.00159  -0.0006   1.0000   1.0000
  -0.250  -0.0264   0.00690   0.00154  -0.0003   1.0000   1.0000
   0.000   0.0001   0.00689   0.00153   0.0000   1.0000   1.0000
   0.250   0.0266   0.00690   0.00154   0.0003   1.0000   1.0000
   0.500   0.0530   0.00691   0.00159   0.0006   1.0000   1.0000
   0.750   0.0795   0.00693   0.00165   0.0010   1.0000   1.0000
   1.000   0.1058   0.00696   0.00173   0.0013   1.0000   1.0000
   1.250   0.1321   0.00699   0.00185   0.0017   1.0000   1.0000
   1.500   0.1582   0.00704   0.00201   0.0020   1.0000   1.0000
   1.750   0.1845   0.00710   0.00219   0.0023   0.9994   1.0000
   2.000   0.2410   0.00728   0.00231  -0.0027   0.8412   1.0000
   2.250   0.2575   0.00802   0.00233   0.0010   0.6447   1.0000
   2.500   0.2797   0.00896   0.00249   0.0024   0.4592   1.0000
   2.750   0.3048   0.00979   0.00272   0.0026   0.3172   1.0000
   3.000   0.3309   0.01061   0.00303   0.0027   0.2019   1.0000
   3.250   0.3573   0.01156   0.00353   0.0026   0.1217   1.0000
   3.500   0.3843   0.01240   0.00426   0.0028   0.0863   1.0000
   3.750   0.4108   0.01342   0.00515   0.0030   0.0681   1.0000
   4.000   0.4380   0.01421   0.00599   0.0034   0.0588   1.0000
   4.250   0.4647   0.01533   0.00715   0.0037   0.0512   1.0000
   4.500   0.4916   0.01642   0.00829   0.0041   0.0462   1.0000
   4.750   0.5175   0.01901   0.01104   0.0045   0.0430   1.0000
   5.000   0.5453   0.01984   0.01217   0.0050   0.0397   1.0000
   5.250   0.5722   0.02185   0.01454   0.0055   0.0378   1.0000
   5.500   0.5986   0.02485   0.01806   0.0060   0.0375   1.0000
   5.750   0.6231   0.02954   0.02344   0.0065   0.0397   1.0000
   6.000   0.6449   0.03447   0.02891   0.0065   0.0411   1.0000
   6.250   0.6660   0.04641   0.04156   0.0065   0.0692   1.0000
   6.500   0.6831   0.05248   0.04848   0.0030   0.0605   1.0000
   6.750   0.6993   0.05590   0.05198   0.0024   0.0581   1.0000
   7.000   0.7139   0.05915   0.05521   0.0028   0.0566   1.0000
   7.250   0.7181   0.06738   0.06347   0.0008   0.0553   1.0000
   7.500   0.7283   0.07648   0.07314  -0.0132   0.0517   1.0000
   7.750   0.7348   0.08289   0.07960  -0.0204   0.0497   1.0000
   8.000   0.7388   0.08833   0.08504  -0.0261   0.0482   1.0000
   8.250   0.7394   0.09278   0.08946  -0.0294   0.0470   1.0000
   8.500   0.7417   0.09672   0.09338  -0.0312   0.0460   1.0000
   8.750   0.7465   0.10016   0.09682  -0.0313   0.0449   1.0000
   9.000   0.7533   0.10351   0.10018  -0.0283   0.0438   1.0000
   9.250   0.6069   0.10119   0.09789  -0.0259   0.0485   1.0000
   9.500   0.6065   0.10531   0.10199  -0.0268   0.0472   1.0000
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