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HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il)
Reynolds number: 200,000
Max Cl/Cd: 79.57 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq259b-il-200000.txt
Download as CSV file: xf-hq259b-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9 B AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4217   0.08850   0.08495  -0.0365   1.0000   0.0467
  -8.500  -0.4351   0.08455   0.08111  -0.0416   1.0000   0.0477
  -8.250  -0.4473   0.08073   0.07737  -0.0443   1.0000   0.0478
  -8.000  -0.4595   0.07644   0.07305  -0.0486   1.0000   0.0480
  -7.750  -0.4706   0.07353   0.07008  -0.0491   1.0000   0.0481
  -7.500  -0.4811   0.07101   0.06748  -0.0481   1.0000   0.0482
  -7.250  -0.4961   0.06535   0.06184  -0.0471   1.0000   0.0489
  -7.000  -0.4946   0.06218   0.05880  -0.0444   1.0000   0.0498
  -6.750  -0.4930   0.06079   0.05751  -0.0413   1.0000   0.0513
  -6.500  -0.4935   0.05890   0.05561  -0.0395   1.0000   0.0532
  -6.250  -0.4734   0.05454   0.05105  -0.0440   0.9970   0.0571
  -6.000  -0.4415   0.04735   0.04325  -0.0527   0.9915   0.0628
  -5.750  -0.4144   0.04413   0.04005  -0.0551   0.9877   0.0654
  -5.500  -0.3765   0.04046   0.03563  -0.0605   0.9837   0.0758
  -5.250  -0.3521   0.03690   0.03219  -0.0620   0.9796   0.0787
  -5.000  -0.3202   0.03439   0.02924  -0.0648   0.9751   0.0909
  -4.750  -0.2872   0.03212   0.02678  -0.0674   0.9721   0.1054
  -4.500  -0.2408   0.02406   0.01728  -0.0673   0.9707   0.0475
  -4.250  -0.2108   0.02184   0.01474  -0.0679   0.9666   0.0472
  -4.000  -0.1790   0.02039   0.01296  -0.0687   0.9627   0.0489
  -3.750  -0.1456   0.01858   0.01099  -0.0698   0.9601   0.0496
  -3.500  -0.1109   0.01726   0.00963  -0.0713   0.9579   0.0516
  -3.250  -0.0739   0.01646   0.00882  -0.0732   0.9559   0.0556
  -3.000  -0.0487   0.01598   0.00828  -0.0728   0.9499   0.0599
  -2.750  -0.0166   0.01504   0.00738  -0.0738   0.9465   0.0655
  -2.500   0.0190   0.01439   0.00676  -0.0756   0.9439   0.0785
  -2.250   0.0560   0.01313   0.00605  -0.0781   0.9420   0.1953
  -2.000   0.0746   0.01183   0.00632  -0.0770   0.9364   0.6227
  -1.750   0.1084   0.01173   0.00637  -0.0775   0.9313   0.7005
  -1.500   0.1510   0.01149   0.00623  -0.0794   0.9274   0.7565
  -1.250   0.1772   0.01139   0.00617  -0.0782   0.9183   0.7888
  -1.000   0.2108   0.01119   0.00601  -0.0781   0.9133   0.8244
  -0.750   0.2320   0.01110   0.00597  -0.0758   0.9046   0.8529
  -0.500   0.2627   0.01091   0.00575  -0.0758   0.8995   0.8708
  -0.250   0.2879   0.01080   0.00564  -0.0749   0.8932   0.8868
   0.000   0.3140   0.01064   0.00549  -0.0741   0.8869   0.9044
   0.250   0.3462   0.01041   0.00525  -0.0744   0.8825   0.9232
   0.500   0.3768   0.01031   0.00517  -0.0748   0.8745   0.9468
   0.750   0.4223   0.01008   0.00493  -0.0782   0.8696   0.9701
   1.000   0.4615   0.01000   0.00484  -0.0808   0.8617   1.0000
   1.250   0.4917   0.00993   0.00471  -0.0812   0.8544   1.0000
   1.500   0.5187   0.00995   0.00472  -0.0812   0.8444   1.0000
   1.750   0.5478   0.00992   0.00466  -0.0813   0.8354   1.0000
   2.000   0.5763   0.00988   0.00459  -0.0811   0.8253   1.0000
   2.250   0.6031   0.00987   0.00458  -0.0807   0.8133   1.0000
   2.500   0.6302   0.00985   0.00454  -0.0802   0.8005   1.0000
   2.750   0.6571   0.00981   0.00451  -0.0796   0.7861   1.0000
   3.000   0.6838   0.00976   0.00445  -0.0789   0.7693   1.0000
   3.250   0.7097   0.00970   0.00437  -0.0779   0.7475   1.0000
   3.500   0.7343   0.00965   0.00427  -0.0767   0.7145   1.0000
   3.750   0.7582   0.00967   0.00419  -0.0754   0.6711   1.0000
   4.000   0.7814   0.00982   0.00415  -0.0740   0.6089   1.0000
   4.250   0.8021   0.01028   0.00421  -0.0724   0.5349   1.0000
   4.500   0.8229   0.01092   0.00453  -0.0710   0.4807   1.0000
   4.750   0.8449   0.01151   0.00491  -0.0700   0.4412   1.0000
   5.000   0.8679   0.01202   0.00531  -0.0692   0.4094   1.0000
   5.250   0.8910   0.01251   0.00571  -0.0685   0.3800   1.0000
   5.500   0.9134   0.01302   0.00612  -0.0676   0.3452   1.0000
   5.750   0.9352   0.01354   0.00650  -0.0667   0.3031   1.0000
   6.000   0.9563   0.01415   0.00693  -0.0657   0.2532   1.0000
   6.250   0.9751   0.01505   0.00748  -0.0645   0.1853   1.0000
   6.500   0.9926   0.01621   0.00831  -0.0632   0.1328   1.0000
   6.750   1.0110   0.01731   0.00922  -0.0619   0.1040   1.0000
   7.000   1.0294   0.01841   0.01023  -0.0606   0.0827   1.0000
   7.250   1.0470   0.01963   0.01141  -0.0590   0.0680   1.0000
   7.500   1.0642   0.02097   0.01273  -0.0574   0.0594   1.0000
   7.750   1.0830   0.02207   0.01384  -0.0562   0.0531   1.0000
   8.000   1.1015   0.02359   0.01541  -0.0548   0.0492   1.0000
   8.250   1.1224   0.02477   0.01670  -0.0538   0.0458   1.0000
   8.500   1.1422   0.02597   0.01791  -0.0528   0.0425   1.0000
   8.750   1.1631   0.02820   0.02022  -0.0520   0.0398   1.0000
   9.000   1.1847   0.02973   0.02199  -0.0511   0.0381   1.0000
   9.250   1.2049   0.03129   0.02373  -0.0500   0.0359   1.0000
   9.500   1.2230   0.03261   0.02516  -0.0489   0.0338   1.0000
   9.750   1.2417   0.03528   0.02791  -0.0483   0.0320   1.0000
  10.000   1.2554   0.03917   0.03218  -0.0468   0.0311   1.0000
  10.250   1.2654   0.04164   0.03504  -0.0447   0.0306   1.0000
  10.500   1.2710   0.04436   0.03817  -0.0422   0.0299   1.0000
  10.750   1.2721   0.04714   0.04134  -0.0394   0.0290   1.0000
  11.000   1.2683   0.05006   0.04459  -0.0363   0.0283   1.0000
  11.250   1.2581   0.05306   0.04789  -0.0328   0.0280   1.0000
  11.500   1.2431   0.05647   0.05158  -0.0295   0.0279   1.0000
  11.750   1.2239   0.06045   0.05584  -0.0270   0.0280   1.0000
  12.000   1.2023   0.06491   0.06057  -0.0256   0.0281   1.0000
  12.250   1.1787   0.07002   0.06592  -0.0255   0.0283   1.0000
  12.500   1.1539   0.07583   0.07196  -0.0268   0.0286   1.0000
  12.750   1.1282   0.08250   0.07882  -0.0296   0.0289   1.0000
  13.000   1.1011   0.09039   0.08687  -0.0341   0.0293   1.0000
  13.250   1.0734   0.09981   0.09643  -0.0406   0.0297   1.0000
  13.500   1.0466   0.11050   0.10722  -0.0479   0.0305   1.0000
  13.750   1.0249   0.12090   0.11765  -0.0538   0.0312   1.0000
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