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HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/9 AIRFOIL (hq309-il)
Reynolds number: 50,000
Max Cl/Cd: 41.07 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq309-il-50000-n5.txt
Download as CSV file: xf-hq309-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/9 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3750   0.09883   0.09220  -0.0338   1.0000   0.1056
  -8.000  -0.3986   0.09803   0.09163  -0.0359   1.0000   0.1106
  -7.750  -0.4159   0.09609   0.08990  -0.0387   1.0000   0.1112
  -7.250  -0.3937   0.08529   0.07906  -0.0363   1.0000   0.0634
  -7.000  -0.3993   0.08092   0.07476  -0.0388   1.0000   0.0522
  -6.750  -0.4026   0.07752   0.07143  -0.0394   1.0000   0.0500
  -6.500  -0.4065   0.07373   0.06767  -0.0408   1.0000   0.0477
  -6.250  -0.4087   0.06830   0.06193  -0.0464   1.0000   0.0425
  -6.000  -0.4053   0.06497   0.05864  -0.0454   1.0000   0.0417
  -5.750  -0.4006   0.06146   0.05507  -0.0455   1.0000   0.0409
  -5.500  -0.3930   0.05779   0.05127  -0.0461   1.0000   0.0402
  -5.250  -0.3822   0.05399   0.04727  -0.0470   1.0000   0.0395
  -5.000  -0.3678   0.05012   0.04311  -0.0482   1.0000   0.0389
  -4.750  -0.3502   0.04639   0.03903  -0.0493   1.0000   0.0385
  -4.500  -0.3295   0.04276   0.03496  -0.0503   1.0000   0.0382
  -4.250  -0.3066   0.03944   0.03115  -0.0511   1.0000   0.0383
  -4.000  -0.2819   0.03659   0.02776  -0.0517   1.0000   0.0400
  -3.750  -0.2553   0.03432   0.02473  -0.0518   1.0000   0.0427
  -3.500  -0.2260   0.03175   0.02195  -0.0531   0.9977   0.0457
  -3.250  -0.1905   0.02967   0.01941  -0.0547   0.9937   0.0483
  -3.000  -0.1561   0.02790   0.01725  -0.0555   0.9893   0.0522
  -2.750  -0.1220   0.02656   0.01572  -0.0567   0.9851   0.0625
  -2.500  -0.0908   0.02539   0.01438  -0.0572   0.9796   0.0758
  -2.250  -0.0556   0.02431   0.01318  -0.0588   0.9749   0.1031
  -2.000  -0.0205   0.02322   0.01213  -0.0608   0.9697   0.1465
  -1.750   0.0086   0.02088   0.01183  -0.0619   0.9656   0.5616
  -1.500   0.0264   0.02066   0.01203  -0.0580   0.9589   0.7738
  -1.250   0.0561   0.02004   0.01157  -0.0567   0.9505   1.0000
  -1.000   0.0943   0.02031   0.01137  -0.0595   0.9439   1.0000
  -0.750   0.1288   0.02056   0.01121  -0.0616   0.9360   1.0000
  -0.500   0.1641   0.02084   0.01116  -0.0637   0.9285   1.0000
  -0.250   0.2004   0.02111   0.01116  -0.0658   0.9210   1.0000
   0.000   0.2327   0.02139   0.01121  -0.0673   0.9122   1.0000
   0.250   0.2723   0.02165   0.01125  -0.0699   0.9053   1.0000
   0.500   0.3024   0.02192   0.01136  -0.0708   0.8952   1.0000
   0.750   0.3361   0.02217   0.01149  -0.0723   0.8862   1.0000
   1.000   0.3746   0.02238   0.01158  -0.0745   0.8783   1.0000
   1.250   0.4045   0.02263   0.01176  -0.0751   0.8676   1.0000
   1.500   0.4370   0.02285   0.01194  -0.0762   0.8576   1.0000
   1.750   0.4761   0.02295   0.01203  -0.0782   0.8497   1.0000
   2.000   0.5054   0.02315   0.01223  -0.0785   0.8381   1.0000
   2.250   0.5356   0.02330   0.01239  -0.0789   0.8260   1.0000
   2.500   0.5672   0.02335   0.01247  -0.0792   0.8132   1.0000
   2.750   0.5992   0.02331   0.01254  -0.0795   0.7995   1.0000
   3.000   0.6307   0.02325   0.01254  -0.0796   0.7855   1.0000
   3.250   0.6617   0.02317   0.01254  -0.0795   0.7711   1.0000
   3.500   0.6925   0.02307   0.01253  -0.0794   0.7563   1.0000
   3.750   0.7237   0.02289   0.01254  -0.0791   0.7407   1.0000
   4.000   0.7493   0.02289   0.01265  -0.0781   0.7211   1.0000
   4.250   0.7783   0.02271   0.01259  -0.0774   0.7015   1.0000
   4.500   0.8049   0.02263   0.01264  -0.0763   0.6790   1.0000
   4.750   0.8327   0.02249   0.01262  -0.0754   0.6551   1.0000
   5.000   0.8588   0.02246   0.01278  -0.0742   0.6278   1.0000
   5.250   0.8836   0.02252   0.01295  -0.0729   0.5965   1.0000
   5.500   0.9092   0.02259   0.01307  -0.0716   0.5621   1.0000
   5.750   0.9326   0.02284   0.01334  -0.0701   0.5233   1.0000
   6.000   0.9549   0.02325   0.01370  -0.0686   0.4825   1.0000
   6.250   0.9757   0.02386   0.01430  -0.0670   0.4412   1.0000
   6.500   0.9949   0.02464   0.01500  -0.0654   0.4018   1.0000
   6.750   1.0131   0.02556   0.01584  -0.0637   0.3649   1.0000
   7.000   1.0301   0.02657   0.01681  -0.0621   0.3296   1.0000
   7.250   1.0459   0.02767   0.01784  -0.0604   0.2964   1.0000
   7.500   1.0607   0.02883   0.01899  -0.0587   0.2638   1.0000
   7.750   1.0744   0.03007   0.02022  -0.0570   0.2330   1.0000
   8.000   1.0872   0.03137   0.02162  -0.0552   0.2041   1.0000
   8.250   1.0990   0.03279   0.02305  -0.0534   0.1767   1.0000
   8.500   1.1101   0.03434   0.02463  -0.0516   0.1507   1.0000
   8.750   1.1224   0.03611   0.02647  -0.0498   0.1287   1.0000
   9.000   1.1297   0.03789   0.02822  -0.0477   0.1097   1.0000
   9.250   1.1389   0.03992   0.03034  -0.0457   0.0927   1.0000
   9.500   1.1443   0.04205   0.03256  -0.0436   0.0769   1.0000
   9.750   1.1443   0.04419   0.03472  -0.0416   0.0620   1.0000
  10.000   1.1462   0.04681   0.03745  -0.0398   0.0509   1.0000
  10.250   1.1464   0.04962   0.04039  -0.0382   0.0423   1.0000
  10.500   1.1463   0.05250   0.04338  -0.0368   0.0371   1.0000
  10.750   1.1473   0.05578   0.04688  -0.0355   0.0333   1.0000
  11.000   1.1486   0.05915   0.05060  -0.0343   0.0301   1.0000
  11.250   1.1467   0.06274   0.05443  -0.0336   0.0281   1.0000
  11.500   1.1432   0.06655   0.05846  -0.0332   0.0269   1.0000
  11.750   1.1379   0.07069   0.06280  -0.0331   0.0261   1.0000
  12.000   1.1298   0.07535   0.06766  -0.0336   0.0254   1.0000
  12.250   1.1205   0.08041   0.07306  -0.0346   0.0251   1.0000
  12.500   1.1080   0.08614   0.07899  -0.0363   0.0249   1.0000
  12.750   1.0942   0.09232   0.08542  -0.0390   0.0248   1.0000
  13.000   1.0792   0.09911   0.09231  -0.0424   0.0249   1.0000
  13.500   1.0465   0.11515   0.10886  -0.0520   0.0254   1.0000
  13.750   1.0182   0.12862   0.12263  -0.0609   0.0268   1.0000
  14.000   0.9902   0.14392   0.13797  -0.0699   0.0294   1.0000
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