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HT12 (ht12-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HT12 (ht12-il)
Reynolds number: 200,000
Max Cl/Cd: 32.3 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ht12-il-200000.txt
Download as CSV file: xf-ht12-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.7449   0.09514   0.09180   0.0366   1.0000   0.0489
  -8.000  -0.7447   0.09055   0.08725   0.0332   1.0000   0.0503
  -7.750  -0.7421   0.08482   0.08153   0.0265   1.0000   0.0521
  -7.500  -0.7332   0.07317   0.06959   0.0054   1.0000   0.0554
  -7.250  -0.7318   0.06432   0.06055   0.0006   1.0000   0.0564
  -7.000  -0.7186   0.06101   0.05736   0.0019   1.0000   0.0577
  -6.750  -0.7038   0.05788   0.05419   0.0016   1.0000   0.0596
  -6.500  -0.6873   0.05337   0.04950  -0.0006   1.0000   0.0628
  -6.250  -0.6704   0.03742   0.03235  -0.0060   1.0000   0.0404
  -6.000  -0.6493   0.03202   0.02638  -0.0066   1.0000   0.0394
  -5.750  -0.6256   0.02715   0.02083  -0.0066   1.0000   0.0381
  -5.500  -0.5998   0.02324   0.01627  -0.0062   1.0000   0.0373
  -5.250  -0.5731   0.02079   0.01340  -0.0057   1.0000   0.0384
  -5.000  -0.5458   0.01918   0.01147  -0.0053   1.0000   0.0412
  -4.750  -0.5186   0.01756   0.00957  -0.0049   1.0000   0.0445
  -4.500  -0.4922   0.01588   0.00784  -0.0045   1.0000   0.0484
  -4.250  -0.4649   0.01497   0.00682  -0.0041   1.0000   0.0542
  -4.000  -0.4383   0.01380   0.00568  -0.0039   1.0000   0.0630
  -3.750  -0.4113   0.01281   0.00471  -0.0036   1.0000   0.0749
  -3.500  -0.3841   0.01197   0.00393  -0.0034   1.0000   0.0987
  -3.250  -0.3571   0.01105   0.00329  -0.0033   1.0000   0.1508
  -3.000  -0.3304   0.01025   0.00293  -0.0033   1.0000   0.2412
  -2.750  -0.3035   0.00971   0.00270  -0.0033   1.0000   0.3247
  -2.500  -0.2768   0.00924   0.00251  -0.0031   1.0000   0.3998
  -2.250  -0.2505   0.00873   0.00229  -0.0027   1.0000   0.4816
  -2.000  -0.2262   0.00801   0.00214  -0.0019   1.0000   0.6033
  -1.750  -0.2093   0.00713   0.00210   0.0015   1.0000   0.8148
  -1.500  -0.1625   0.00683   0.00194  -0.0015   1.0000   1.0000
  -1.250  -0.1355   0.00680   0.00178  -0.0012   1.0000   1.0000
  -1.000  -0.1084   0.00677   0.00167  -0.0010   1.0000   1.0000
  -0.750  -0.0813   0.00674   0.00158  -0.0007   1.0000   1.0000
  -0.500  -0.0542   0.00673   0.00152  -0.0005   1.0000   1.0000
  -0.250  -0.0271   0.00672   0.00148  -0.0002   1.0000   1.0000
   0.000   0.0001   0.00672   0.00147   0.0000   1.0000   1.0000
   0.250   0.0272   0.00672   0.00148   0.0002   1.0000   1.0000
   0.500   0.0544   0.00673   0.00152   0.0005   1.0000   1.0000
   0.750   0.0815   0.00674   0.00158   0.0007   1.0000   1.0000
   1.000   0.1086   0.00677   0.00167   0.0010   1.0000   1.0000
   1.250   0.1356   0.00680   0.00178   0.0012   1.0000   1.0000
   1.500   0.1627   0.00683   0.00194   0.0015   1.0000   1.0000
   1.750   0.2094   0.00714   0.00210  -0.0015   0.8133   1.0000
   2.000   0.2263   0.00802   0.00214   0.0019   0.6024   1.0000
   2.250   0.2507   0.00873   0.00230   0.0027   0.4813   1.0000
   2.500   0.2770   0.00924   0.00251   0.0031   0.3992   1.0000
   2.750   0.3037   0.00972   0.00271   0.0033   0.3242   1.0000
   3.000   0.3305   0.01026   0.00293   0.0033   0.2406   1.0000
   3.250   0.3572   0.01106   0.00329   0.0033   0.1505   1.0000
   3.500   0.3843   0.01197   0.00393   0.0034   0.0986   1.0000
   3.750   0.4115   0.01282   0.00472   0.0036   0.0749   1.0000
   4.000   0.4385   0.01380   0.00569   0.0039   0.0629   1.0000
   4.250   0.4651   0.01497   0.00682   0.0041   0.0541   1.0000
   4.500   0.4924   0.01589   0.00785   0.0045   0.0483   1.0000
   4.750   0.5189   0.01755   0.00956   0.0049   0.0444   1.0000
   5.000   0.5460   0.01920   0.01150   0.0053   0.0412   1.0000
   5.250   0.5733   0.02082   0.01342   0.0057   0.0384   1.0000
   5.500   0.6000   0.02327   0.01630   0.0062   0.0373   1.0000
   5.750   0.6258   0.02718   0.02087   0.0065   0.0381   1.0000
   6.000   0.6495   0.03206   0.02643   0.0065   0.0394   1.0000
   6.250   0.6707   0.03744   0.03238   0.0060   0.0404   1.0000
   6.500   0.6875   0.05341   0.04955   0.0005   0.0628   1.0000
   6.750   0.7041   0.05796   0.05427  -0.0017   0.0595   1.0000
   7.000   0.7189   0.06109   0.05743  -0.0020   0.0576   1.0000
   7.250   0.7320   0.06437   0.06060  -0.0007   0.0563   1.0000
   7.500   0.7335   0.07321   0.06964  -0.0054   0.0553   1.0000
   7.750   0.7425   0.08486   0.08158  -0.0265   0.0521   1.0000
   8.000   0.7451   0.09063   0.08733  -0.0333   0.0503   1.0000
   8.250   0.7454   0.09522   0.09188  -0.0368   0.0488   1.0000
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