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HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/9 AIRFOIL (hq359-il)
Reynolds number: 100,000
Max Cl/Cd: 63.24 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq359-il-100000.txt
Download as CSV file: xf-hq359-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3769   0.09940   0.09497  -0.0369   1.0000   0.0667
  -7.750  -0.3946   0.09834   0.09403  -0.0356   1.0000   0.0668
  -7.500  -0.4073   0.09645   0.09222  -0.0368   1.0000   0.0669
  -7.250  -0.4176   0.09410   0.08992  -0.0393   1.0000   0.0671
  -7.000  -0.4011   0.08885   0.08473  -0.0281   1.0000   0.0698
  -6.750  -0.4051   0.08667   0.08260  -0.0260   1.0000   0.0713
  -6.500  -0.4112   0.08442   0.08042  -0.0251   1.0000   0.0728
  -6.250  -0.4166   0.08188   0.07792  -0.0253   1.0000   0.0748
  -6.000  -0.4195   0.07892   0.07500  -0.0273   1.0000   0.0767
  -5.750  -0.4158   0.07505   0.07092  -0.0385   1.0000   0.0804
  -5.500  -0.4118   0.07047   0.06632  -0.0399   1.0000   0.0817
  -5.250  -0.4088   0.06752   0.06351  -0.0360   1.0000   0.0838
  -5.000  -0.4013   0.06472   0.06071  -0.0356   1.0000   0.0875
  -4.750  -0.3793   0.05999   0.05557  -0.0439   1.0000   0.0958
  -4.500  -0.3718   0.05699   0.05272  -0.0417   1.0000   0.0990
  -4.250  -0.3490   0.05320   0.04862  -0.0462   1.0000   0.1104
  -4.000  -0.3304   0.05020   0.04548  -0.0478   1.0000   0.1244
  -3.750  -0.3141   0.04738   0.04263  -0.0481   1.0000   0.1400
  -3.500  -0.2931   0.04478   0.03989  -0.0498   1.0000   0.1666
  -2.750  -0.1325   0.03110   0.02356  -0.0631   0.9898   0.0660
  -2.500  -0.0916   0.02801   0.02008  -0.0656   0.9860   0.0601
  -2.250  -0.0475   0.02597   0.01747  -0.0679   0.9825   0.0579
  -2.000  -0.0128   0.02482   0.01611  -0.0691   0.9766   0.0626
  -1.750   0.0265   0.02351   0.01463  -0.0710   0.9719   0.0718
  -1.500   0.0648   0.02232   0.01348  -0.0728   0.9672   0.0959
  -1.250   0.0992   0.02109   0.01266  -0.0746   0.9610   0.1709
  -1.000   0.1190   0.01906   0.01304  -0.0711   0.9568   0.8207
  -0.750   0.1532   0.01875   0.01269  -0.0720   0.9482   1.0000
  -0.500   0.1995   0.01919   0.01276  -0.0761   0.9421   1.0000
  -0.250   0.2318   0.01947   0.01279  -0.0776   0.9326   1.0000
   0.000   0.2707   0.01981   0.01291  -0.0802   0.9249   1.0000
   0.250   0.3096   0.02011   0.01300  -0.0827   0.9169   1.0000
   0.500   0.3424   0.02041   0.01316  -0.0842   0.9077   1.0000
   0.750   0.3897   0.02060   0.01322  -0.0879   0.9013   1.0000
   1.000   0.4242   0.02070   0.01322  -0.0892   0.8897   1.0000
   1.250   0.4652   0.02061   0.01305  -0.0913   0.8777   1.0000
   1.500   0.5091   0.02033   0.01272  -0.0937   0.8659   1.0000
   1.750   0.5574   0.01995   0.01234  -0.0968   0.8571   1.0000
   2.000   0.5987   0.01969   0.01207  -0.0988   0.8484   1.0000
   2.250   0.6314   0.01959   0.01198  -0.0992   0.8374   1.0000
   2.500   0.6677   0.01935   0.01176  -0.1002   0.8277   1.0000
   2.750   0.7097   0.01881   0.01131  -0.1017   0.8198   1.0000
   3.000   0.7409   0.01857   0.01111  -0.1016   0.8075   1.0000
   3.250   0.7728   0.01823   0.01083  -0.1015   0.7949   1.0000
   3.500   0.8050   0.01784   0.01050  -0.1012   0.7816   1.0000
   3.750   0.8372   0.01739   0.01018  -0.1009   0.7672   1.0000
   4.000   0.8697   0.01690   0.00975  -0.1005   0.7515   1.0000
   4.250   0.8961   0.01664   0.00957  -0.0993   0.7306   1.0000
   4.500   0.9262   0.01623   0.00919  -0.0985   0.7085   1.0000
   4.750   0.9525   0.01599   0.00905  -0.0971   0.6799   1.0000
   5.000   0.9777   0.01585   0.00890  -0.0956   0.6442   1.0000
   5.250   1.0018   0.01587   0.00882  -0.0940   0.6003   1.0000
   5.500   1.0232   0.01618   0.00895  -0.0921   0.5480   1.0000
   5.750   1.0437   0.01677   0.00928  -0.0903   0.4974   1.0000
   6.000   1.0642   0.01754   0.00986  -0.0888   0.4554   1.0000
   6.250   1.0852   0.01838   0.01050  -0.0875   0.4218   1.0000
   6.500   1.1064   0.01922   0.01123  -0.0864   0.3927   1.0000
   6.750   1.1275   0.02004   0.01200  -0.0853   0.3666   1.0000
   7.000   1.1482   0.02085   0.01284  -0.0841   0.3421   1.0000
   7.250   1.1685   0.02169   0.01371  -0.0829   0.3187   1.0000
   7.500   1.1878   0.02257   0.01465  -0.0816   0.2950   1.0000
   7.750   1.2029   0.02336   0.01546  -0.0796   0.2667   1.0000
   8.000   1.2104   0.02384   0.01596  -0.0768   0.2303   1.0000
   8.250   1.2188   0.02436   0.01651  -0.0741   0.1874   1.0000
   8.500   1.2202   0.02621   0.01778  -0.0707   0.0980   1.0000
   8.750   1.2119   0.02973   0.02079  -0.0657   0.0529   1.0000
   9.000   1.2118   0.03207   0.02316  -0.0618   0.0445   1.0000
   9.250   1.2161   0.03417   0.02532  -0.0587   0.0395   1.0000
   9.500   1.2230   0.03696   0.02810  -0.0562   0.0362   1.0000
   9.750   1.2376   0.03898   0.03035  -0.0544   0.0328   1.0000
  10.000   1.2504   0.04116   0.03266  -0.0528   0.0299   1.0000
  10.250   1.2691   0.04425   0.03585  -0.0520   0.0281   1.0000
  10.500   1.2934   0.04853   0.04047  -0.0519   0.0274   1.0000
  10.750   1.3061   0.05275   0.04505  -0.0506   0.0272   1.0000
  11.000   1.3086   0.05624   0.04891  -0.0482   0.0273   1.0000
  11.250   1.3047   0.05954   0.05255  -0.0455   0.0274   1.0000
  11.500   1.2964   0.06273   0.05609  -0.0427   0.0277   1.0000
  11.750   1.2838   0.06622   0.05994  -0.0403   0.0280   1.0000
  12.000   1.2680   0.07023   0.06430  -0.0386   0.0284   1.0000
  12.250   1.2490   0.07481   0.06923  -0.0377   0.0288   1.0000
  12.500   1.2263   0.08006   0.07480  -0.0380   0.0292   1.0000
  12.750   1.2008   0.08607   0.08110  -0.0395   0.0296   1.0000
  13.000   1.1747   0.09292   0.08821  -0.0425   0.0300   1.0000
  13.250   1.1483   0.10072   0.09624  -0.0470   0.0304   1.0000
  13.500   1.1210   0.10985   0.10557  -0.0531   0.0308   1.0000
  13.750   1.0923   0.12089   0.11670  -0.0611   0.0314   1.0000
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