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HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il)
Reynolds number: 100,000
Max Cl/Cd: 55.11 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2090sm-il-100000.txt
Download as CSV file: xf-hq2090sm-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ-2.0/9  9.0%   smoothed                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4806   0.11981   0.11470  -0.0174   1.0000   0.0777
 -10.250  -0.4929   0.11739   0.11237  -0.0228   1.0000   0.0787
 -10.000  -0.5020   0.11438   0.10945  -0.0273   1.0000   0.0790
  -9.750  -0.4660   0.10790   0.10285  -0.0199   1.0000   0.0832
  -9.500  -0.4612   0.10460   0.09958  -0.0207   1.0000   0.0869
  -9.250  -0.4642   0.10126   0.09631  -0.0235   1.0000   0.0903
  -9.000  -0.4803   0.09815   0.09332  -0.0296   1.0000   0.0921
  -8.750  -0.4673   0.09341   0.08860  -0.0273   1.0000   0.0953
  -8.500  -0.4581   0.09052   0.08572  -0.0265   1.0000   0.1011
  -8.250  -0.4662   0.08703   0.08233  -0.0297   1.0000   0.1042
  -8.000  -0.4884   0.08287   0.07830  -0.0368   1.0000   0.1057
  -7.750  -0.4762   0.07950   0.07497  -0.0325   1.0000   0.1102
  -7.500  -0.4767   0.07603   0.07155  -0.0344   1.0000   0.1167
  -7.250  -0.4960   0.07156   0.06699  -0.0419   1.0000   0.1197
  -7.000  -0.4843   0.06799   0.06356  -0.0384   1.0000   0.1249
  -6.750  -0.4995   0.06521   0.06049  -0.0429   1.0000   0.1342
  -6.500  -0.4873   0.06097   0.05649  -0.0396   1.0000   0.1383
  -6.250  -0.4924   0.05791   0.05322  -0.0408   1.0000   0.1499
  -6.000  -0.4817   0.05507   0.05053  -0.0377   1.0000   0.1555
  -5.750  -0.4790   0.05209   0.04748  -0.0370   1.0000   0.1676
  -5.250  -0.4388   0.03595   0.02883  -0.0399   1.0000   0.0659
  -5.000  -0.4216   0.03211   0.02484  -0.0390   1.0000   0.0631
  -4.750  -0.4018   0.02934   0.02161  -0.0380   1.0000   0.0632
  -4.500  -0.3804   0.02759   0.01925  -0.0367   1.0000   0.0657
  -4.250  -0.3581   0.02459   0.01598  -0.0360   1.0000   0.0675
  -4.000  -0.3357   0.02288   0.01411  -0.0351   1.0000   0.0723
  -3.750  -0.3123   0.02148   0.01244  -0.0342   1.0000   0.0809
  -3.500  -0.2893   0.02027   0.01117  -0.0333   1.0000   0.0899
  -3.250  -0.2667   0.01917   0.01008  -0.0325   1.0000   0.1031
  -3.000  -0.2445   0.01821   0.00914  -0.0316   1.0000   0.1196
  -2.750  -0.2229   0.01719   0.00831  -0.0308   1.0000   0.1438
  -2.500  -0.2003   0.01577   0.00748  -0.0305   1.0000   0.2274
  -2.250  -0.1921   0.01416   0.00797  -0.0260   1.0000   0.7029
  -2.000  -0.1819   0.01424   0.00817  -0.0217   1.0000   0.7797
  -1.750  -0.1718   0.01426   0.00823  -0.0175   1.0000   0.8360
  -1.500  -0.1595   0.01419   0.00822  -0.0139   1.0000   0.8953
  -1.250  -0.1100   0.01412   0.00803  -0.0185   0.9979   1.0000
  -1.000  -0.0644   0.01449   0.00812  -0.0234   0.9904   1.0000
  -0.750  -0.0172   0.01494   0.00833  -0.0284   0.9832   1.0000
  -0.500   0.0243   0.01525   0.00843  -0.0322   0.9742   1.0000
  -0.250   0.0684   0.01563   0.00865  -0.0362   0.9662   1.0000
   0.000   0.1117   0.01597   0.00885  -0.0400   0.9576   1.0000
   0.250   0.1497   0.01626   0.00904  -0.0427   0.9481   1.0000
   0.500   0.1949   0.01658   0.00927  -0.0466   0.9402   1.0000
   0.750   0.2338   0.01681   0.00945  -0.0492   0.9301   1.0000
   1.000   0.2716   0.01702   0.00963  -0.0515   0.9195   1.0000
   1.250   0.3162   0.01711   0.00971  -0.0548   0.9088   1.0000
   1.500   0.3744   0.01691   0.00956  -0.0601   0.8992   1.0000
   1.750   0.4159   0.01678   0.00947  -0.0623   0.8867   1.0000
   2.000   0.4528   0.01671   0.00945  -0.0636   0.8743   1.0000
   2.500   0.5246   0.01639   0.00928  -0.0653   0.8485   1.0000
   2.750   0.5584   0.01614   0.00910  -0.0654   0.8342   1.0000
   3.000   0.5902   0.01586   0.00890  -0.0650   0.8188   1.0000
   3.250   0.6206   0.01558   0.00872  -0.0643   0.8027   1.0000
   3.500   0.6485   0.01536   0.00857  -0.0631   0.7845   1.0000
   3.750   0.6743   0.01518   0.00847  -0.0616   0.7632   1.0000
   4.000   0.7007   0.01495   0.00831  -0.0601   0.7405   1.0000
   4.250   0.7264   0.01474   0.00818  -0.0585   0.7139   1.0000
   4.500   0.7502   0.01457   0.00805  -0.0566   0.6796   1.0000
   4.750   0.7733   0.01442   0.00787  -0.0545   0.6354   1.0000
   5.000   0.7951   0.01446   0.00779  -0.0524   0.5794   1.0000
   5.250   0.8157   0.01480   0.00792  -0.0503   0.5148   1.0000
   5.500   0.8346   0.01546   0.00824  -0.0483   0.4463   1.0000
   5.750   0.8529   0.01631   0.00878  -0.0465   0.3811   1.0000
   6.000   0.8704   0.01727   0.00945  -0.0449   0.3182   1.0000
   6.250   0.8862   0.01850   0.01030  -0.0431   0.2534   1.0000
   6.500   0.9006   0.02005   0.01146  -0.0412   0.1857   1.0000
   6.750   0.9166   0.02176   0.01283  -0.0394   0.1437   1.0000
   7.000   0.9350   0.02332   0.01423  -0.0380   0.1172   1.0000
   7.250   0.9549   0.02504   0.01588  -0.0368   0.0984   1.0000
   7.500   0.9750   0.02672   0.01757  -0.0357   0.0817   1.0000
   7.750   0.9968   0.02891   0.01980  -0.0347   0.0695   1.0000
   8.000   1.0181   0.03131   0.02227  -0.0338   0.0595   1.0000
   8.250   1.0407   0.03383   0.02501  -0.0329   0.0540   1.0000
   8.500   1.0617   0.03801   0.02942  -0.0321   0.0507   1.0000
   8.750   1.0759   0.04044   0.03246  -0.0300   0.0477   1.0000
   9.000   1.0882   0.04345   0.03592  -0.0281   0.0451   1.0000
   9.250   1.0956   0.04737   0.04034  -0.0260   0.0447   1.0000
   9.500   1.0967   0.05175   0.04525  -0.0235   0.0451   1.0000
   9.750   1.0914   0.05637   0.05035  -0.0210   0.0458   1.0000
  10.000   1.0809   0.06098   0.05535  -0.0186   0.0467   1.0000
  10.250   1.0662   0.06531   0.05996  -0.0162   0.0475   1.0000
  10.500   1.0477   0.06934   0.06420  -0.0141   0.0482   1.0000
  10.750   1.0281   0.07368   0.06871  -0.0132   0.0488   1.0000
  11.000   1.0081   0.07860   0.07377  -0.0137   0.0494   1.0000
  11.250   0.9900   0.08410   0.07936  -0.0152   0.0501   1.0000
  11.500   0.8676   0.08621   0.08191  -0.0149   0.0500   1.0000
  11.750   0.8465   0.09367   0.08944  -0.0183   0.0507   1.0000
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