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HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/8 AIRFOIL (hq308-il)
Reynolds number: 200,000
Max Cl/Cd: 86.11 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq308-il-200000.txt
Download as CSV file: xf-hq308-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/8 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3839   0.08982   0.08658  -0.0363   1.0000   0.0290
  -7.500  -0.3900   0.08726   0.08409  -0.0367   1.0000   0.0291
  -7.250  -0.3949   0.08445   0.08134  -0.0378   1.0000   0.0291
  -7.000  -0.3997   0.08158   0.07850  -0.0387   1.0000   0.0291
  -6.750  -0.4038   0.07878   0.07569  -0.0390   1.0000   0.0292
  -6.500  -0.4061   0.07589   0.07277  -0.0393   1.0000   0.0292
  -6.250  -0.4155   0.07003   0.06695  -0.0396   1.0000   0.0298
  -6.000  -0.4186   0.06659   0.06357  -0.0375   1.0000   0.0306
  -5.750  -0.4174   0.06397   0.06098  -0.0361   1.0000   0.0314
  -5.500  -0.3947   0.05982   0.05672  -0.0404   0.9971   0.0330
  -5.250  -0.3611   0.05465   0.05139  -0.0475   0.9930   0.0357
  -5.000  -0.3097   0.05046   0.04656  -0.0567   0.9875   0.0414
  -4.750  -0.2799   0.04315   0.03901  -0.0624   0.9840   0.0431
  -4.500  -0.2520   0.04027   0.03621  -0.0652   0.9809   0.0504
  -4.250  -0.2163   0.03602   0.03145  -0.0691   0.9755   0.0572
  -4.000  -0.1823   0.03310   0.02840  -0.0719   0.9720   0.0622
  -3.750  -0.1423   0.02994   0.02482  -0.0756   0.9694   0.0719
  -3.500  -0.1104   0.02784   0.02236  -0.0772   0.9641   0.0843
  -3.250  -0.0672   0.02237   0.01605  -0.0769   0.9616   0.0356
  -3.000  -0.0270   0.02042   0.01350  -0.0778   0.9586   0.0288
  -2.750   0.0115   0.01814   0.01092  -0.0796   0.9565   0.0284
  -2.250   0.0773   0.01543   0.00806  -0.0814   0.9474   0.0373
  -2.000   0.1159   0.01429   0.00689  -0.0834   0.9443   0.0486
  -1.750   0.1514   0.01169   0.00618  -0.0861   0.9422   0.5471
  -1.500   0.1730   0.01139   0.00634  -0.0841   0.9345   0.7288
  -1.250   0.2083   0.01121   0.00619  -0.0850   0.9307   0.7876
  -1.000   0.2357   0.01097   0.00605  -0.0840   0.9248   0.8486
  -0.750   0.2732   0.01053   0.00576  -0.0848   0.9202   0.9477
  -0.500   0.3239   0.01030   0.00538  -0.0896   0.9169   1.0000
  -0.250   0.3569   0.01026   0.00521  -0.0908   0.9094   1.0000
   0.000   0.3929   0.01016   0.00500  -0.0924   0.9037   1.0000
   0.250   0.4236   0.01011   0.00487  -0.0929   0.8953   1.0000
   0.500   0.4584   0.00990   0.00457  -0.0938   0.8883   1.0000
   0.750   0.4858   0.00985   0.00445  -0.0935   0.8775   1.0000
   1.000   0.5138   0.00981   0.00437  -0.0933   0.8680   1.0000
   1.250   0.5437   0.00973   0.00424  -0.0933   0.8601   1.0000
   1.500   0.5707   0.00971   0.00420  -0.0928   0.8493   1.0000
   1.750   0.5973   0.00965   0.00411  -0.0922   0.8370   1.0000
   2.000   0.6240   0.00959   0.00401  -0.0915   0.8237   1.0000
   2.250   0.6506   0.00956   0.00396  -0.0908   0.8105   1.0000
   2.500   0.6772   0.00955   0.00395  -0.0903   0.7971   1.0000
   2.750   0.7037   0.00956   0.00398  -0.0897   0.7828   1.0000
   3.000   0.7303   0.00956   0.00398  -0.0891   0.7675   1.0000
   3.250   0.7561   0.00960   0.00402  -0.0884   0.7491   1.0000
   3.500   0.7820   0.00965   0.00406  -0.0876   0.7290   1.0000
   3.750   0.8075   0.00972   0.00413  -0.0868   0.7056   1.0000
   4.000   0.8326   0.00983   0.00426  -0.0860   0.6787   1.0000
   4.250   0.8572   0.01000   0.00438  -0.0850   0.6472   1.0000
   4.500   0.8809   0.01023   0.00453  -0.0840   0.6078   1.0000
   4.750   0.9035   0.01057   0.00473  -0.0827   0.5585   1.0000
   5.000   0.9239   0.01110   0.00500  -0.0812   0.4962   1.0000
   5.250   0.9424   0.01184   0.00544  -0.0795   0.4250   1.0000
   5.500   0.9609   0.01266   0.00594  -0.0780   0.3604   1.0000
   5.750   0.9803   0.01344   0.00647  -0.0767   0.3055   1.0000
   6.000   0.9995   0.01427   0.00704  -0.0756   0.2520   1.0000
   6.250   1.0196   0.01504   0.00760  -0.0746   0.2026   1.0000
   6.500   1.0405   0.01577   0.00821  -0.0736   0.1668   1.0000
   6.750   1.0602   0.01665   0.00888  -0.0726   0.1212   1.0000
   7.000   1.0785   0.01776   0.00983  -0.0714   0.0752   1.0000
   7.250   1.0906   0.01979   0.01151  -0.0691   0.0300   1.0000
   7.500   1.1049   0.02152   0.01332  -0.0669   0.0189   1.0000
   7.750   1.1209   0.02292   0.01486  -0.0650   0.0163   1.0000
   8.000   1.1333   0.02480   0.01685  -0.0627   0.0146   1.0000
   8.250   1.1440   0.02774   0.01995  -0.0603   0.0137   1.0000
   8.500   1.1616   0.03050   0.02290  -0.0587   0.0133   1.0000
   8.750   1.1801   0.03322   0.02589  -0.0574   0.0132   1.0000
   9.000   1.1960   0.03653   0.02953  -0.0558   0.0132   1.0000
   9.250   1.2069   0.04053   0.03393  -0.0539   0.0134   1.0000
   9.750   1.2240   0.04658   0.04064  -0.0496   0.0139   1.0000
  10.000   1.2300   0.04876   0.04311  -0.0471   0.0142   1.0000
  10.250   1.2274   0.05152   0.04625  -0.0437   0.0148   1.0000
  10.500   1.2096   0.05592   0.05116  -0.0391   0.0159   1.0000
  10.750   1.1849   0.06059   0.05623  -0.0357   0.0167   1.0000
  11.000   1.1621   0.06535   0.06128  -0.0339   0.0172   1.0000
  11.250   1.1402   0.07033   0.06650  -0.0337   0.0175   1.0000
  11.500   1.1188   0.07578   0.07215  -0.0349   0.0177   1.0000
  11.750   1.0969   0.08201   0.07857  -0.0375   0.0178   1.0000
  12.000   1.0753   0.08912   0.08584  -0.0417   0.0179   1.0000
  12.250   1.0548   0.09727   0.09413  -0.0474   0.0177   1.0000
  12.500   1.0332   0.10737   0.10434  -0.0549   0.0176   1.0000
  12.750   1.0101   0.12032   0.11737  -0.0638   0.0177   1.0000
  13.000   0.9885   0.13469   0.13171  -0.0717   0.0184   1.0000
  13.250   0.9775   0.14425   0.14124  -0.0766   0.0193   1.0000
  13.500   0.9716   0.15194   0.14889  -0.0805   0.0203   1.0000
  13.750   0.9673   0.15838   0.15530  -0.0834   0.0216   1.0000
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