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HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il)
Reynolds number: 500,000
Max Cl/Cd: 97.22 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2090sm-il-500000.txt
Download as CSV file: xf-hq2090sm-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3825   0.10125   0.09908  -0.0219   1.0000   0.0187
 -10.250  -0.3840   0.09639   0.09424  -0.0244   1.0000   0.0196
  -6.500  -0.4695   0.02626   0.02209  -0.0541   0.9883   0.0142
  -6.250  -0.4408   0.02075   0.01603  -0.0561   0.9850   0.0131
  -6.000  -0.4071   0.01761   0.01241  -0.0579   0.9830   0.0132
  -5.750  -0.3758   0.01596   0.01047  -0.0587   0.9786   0.0137
  -5.500  -0.3436   0.01379   0.00803  -0.0599   0.9753   0.0147
  -5.250  -0.3088   0.01272   0.00689  -0.0617   0.9726   0.0163
  -5.000  -0.2727   0.01225   0.00638  -0.0635   0.9701   0.0187
  -4.750  -0.2432   0.01130   0.00533  -0.0640   0.9639   0.0219
  -4.500  -0.2111   0.01072   0.00472  -0.0649   0.9588   0.0267
  -4.250  -0.1812   0.01013   0.00409  -0.0654   0.9528   0.0339
  -4.000  -0.1525   0.00997   0.00389  -0.0655   0.9454   0.0400
  -3.750  -0.1254   0.00947   0.00339  -0.0653   0.9380   0.0500
  -3.500  -0.0989   0.00912   0.00301  -0.0650   0.9299   0.0619
  -3.250  -0.0728   0.00875   0.00270  -0.0646   0.9215   0.0845
  -3.000  -0.0469   0.00826   0.00242  -0.0643   0.9139   0.1470
  -2.750  -0.0232   0.00740   0.00215  -0.0640   0.9044   0.3094
  -2.500   0.0007   0.00669   0.00198  -0.0635   0.8959   0.4892
  -2.250   0.0260   0.00641   0.00192  -0.0629   0.8867   0.5722
  -2.000   0.0519   0.00628   0.00190  -0.0623   0.8770   0.6252
  -1.750   0.0787   0.00625   0.00186  -0.0618   0.8687   0.6585
  -1.500   0.1055   0.00622   0.00184  -0.0614   0.8603   0.6843
  -1.250   0.1326   0.00622   0.00182  -0.0611   0.8522   0.7036
  -1.000   0.1595   0.00621   0.00181  -0.0606   0.8443   0.7226
  -0.750   0.1862   0.00621   0.00180  -0.0602   0.8347   0.7441
  -0.500   0.2120   0.00619   0.00181  -0.0594   0.8244   0.7674
  -0.250   0.2383   0.00619   0.00179  -0.0588   0.8138   0.7847
   0.000   0.2653   0.00616   0.00176  -0.0585   0.8035   0.7947
   0.250   0.2925   0.00614   0.00175  -0.0582   0.7944   0.8050
   0.500   0.3196   0.00614   0.00173  -0.0579   0.7855   0.8160
   0.750   0.3465   0.00613   0.00172  -0.0576   0.7749   0.8276
   1.000   0.3731   0.00610   0.00172  -0.0572   0.7634   0.8399
   1.250   0.3995   0.00608   0.00173  -0.0567   0.7518   0.8537
   1.500   0.4256   0.00606   0.00174  -0.0562   0.7404   0.8703
   1.750   0.4509   0.00603   0.00175  -0.0554   0.7284   0.8908
   2.000   0.4763   0.00599   0.00176  -0.0546   0.7156   0.9211
   2.250   0.5114   0.00596   0.00178  -0.0560   0.7008   0.9639
   2.500   0.5469   0.00601   0.00180  -0.0578   0.6834   1.0000
   2.750   0.5739   0.00611   0.00185  -0.0576   0.6641   1.0000
   3.000   0.6006   0.00624   0.00192  -0.0574   0.6402   1.0000
   3.250   0.6261   0.00644   0.00199  -0.0569   0.6029   1.0000
   3.500   0.6508   0.00672   0.00209  -0.0563   0.5546   1.0000
   3.750   0.6749   0.00710   0.00224  -0.0557   0.5003   1.0000
   4.000   0.6985   0.00756   0.00247  -0.0550   0.4419   1.0000
   4.250   0.7224   0.00804   0.00271  -0.0545   0.3878   1.0000
   4.500   0.7461   0.00854   0.00298  -0.0539   0.3333   1.0000
   4.750   0.7703   0.00900   0.00327  -0.0535   0.2898   1.0000
   5.000   0.7948   0.00944   0.00357  -0.0531   0.2551   1.0000
   5.250   0.8194   0.00988   0.00389  -0.0526   0.2213   1.0000
   5.500   0.8434   0.01037   0.00423  -0.0522   0.1836   1.0000
   5.750   0.8668   0.01095   0.00461  -0.0517   0.1428   1.0000
   6.000   0.8888   0.01169   0.00508  -0.0510   0.0939   1.0000
   6.250   0.9113   0.01238   0.00562  -0.0503   0.0664   1.0000
   6.500   0.9345   0.01297   0.00616  -0.0497   0.0526   1.0000
   6.750   0.9586   0.01344   0.00664  -0.0492   0.0438   1.0000
   7.000   0.9823   0.01394   0.00715  -0.0486   0.0354   1.0000
   7.250   1.0048   0.01460   0.00781  -0.0478   0.0263   1.0000
   7.500   1.0254   0.01553   0.00875  -0.0467   0.0192   1.0000
   7.750   1.0474   0.01622   0.00949  -0.0459   0.0160   1.0000
   8.000   1.0653   0.01743   0.01080  -0.0444   0.0137   1.0000
   8.250   1.0868   0.01812   0.01158  -0.0435   0.0124   1.0000
   8.500   1.1068   0.01898   0.01252  -0.0424   0.0115   1.0000
   8.750   1.1257   0.01994   0.01355  -0.0412   0.0107   1.0000
   9.000   1.1405   0.02143   0.01515  -0.0395   0.0100   1.0000
   9.250   1.1493   0.02411   0.01804  -0.0369   0.0095   1.0000
   9.500   1.1667   0.02534   0.01944  -0.0356   0.0093   1.0000
   9.750   1.1822   0.02688   0.02119  -0.0340   0.0090   1.0000
  10.000   1.1952   0.02883   0.02335  -0.0322   0.0088   1.0000
  10.250   1.2058   0.03104   0.02580  -0.0302   0.0087   1.0000
  10.500   1.2143   0.03315   0.02815  -0.0280   0.0084   1.0000
  10.750   1.2180   0.03519   0.03042  -0.0253   0.0082   1.0000
  11.000   1.2164   0.03748   0.03294  -0.0221   0.0081   1.0000
  11.250   1.2187   0.03879   0.03437  -0.0197   0.0077   1.0000
  11.500   1.2120   0.04150   0.03731  -0.0170   0.0076   1.0000
  11.750   1.2008   0.04478   0.04085  -0.0147   0.0076   1.0000
  12.000   1.1840   0.04892   0.04527  -0.0131   0.0077   1.0000
  12.250   1.1719   0.05262   0.04916  -0.0126   0.0076   1.0000
  12.500   1.1551   0.05731   0.05406  -0.0130   0.0077   1.0000
  12.750   1.1267   0.06435   0.06139  -0.0151   0.0079   1.0000
  13.000   1.1063   0.07092   0.06814  -0.0183   0.0079   1.0000
  13.250   1.0842   0.07876   0.07617  -0.0231   0.0080   1.0000
  13.500   1.0644   0.08720   0.08477  -0.0288   0.0080   1.0000
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