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HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il)
Reynolds number: 200,000
Max Cl/Cd: 75.84 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3011-il-200000-n5.txt
Download as CSV file: xf-hq3011-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/11 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3839   0.08751   0.08404  -0.0452   1.0000   0.0140
  -9.250  -0.3887   0.08385   0.08044  -0.0460   1.0000   0.0137
  -9.000  -0.3995   0.07946   0.07614  -0.0470   1.0000   0.0138
  -8.750  -0.4124   0.07629   0.07307  -0.0466   1.0000   0.0136
  -8.500  -0.4172   0.07014   0.06697  -0.0522   0.9937   0.0135
  -8.250  -0.4161   0.05834   0.05509  -0.0694   0.9787   0.0132
  -8.000  -0.4134   0.04795   0.04435  -0.0802   0.9679   0.0129
  -7.750  -0.4077   0.03826   0.03405  -0.0863   0.9586   0.0127
  -7.500  -0.3977   0.03147   0.02653  -0.0882   0.9490   0.0128
  -7.250  -0.3753   0.02687   0.02122  -0.0899   0.9439   0.0131
  -7.000  -0.3542   0.02404   0.01787  -0.0898   0.9365   0.0136
  -6.750  -0.3271   0.02187   0.01527  -0.0903   0.9316   0.0142
  -6.500  -0.3005   0.02033   0.01346  -0.0906   0.9265   0.0152
  -6.250  -0.2739   0.01953   0.01257  -0.0909   0.9206   0.0165
  -6.000  -0.2448   0.01849   0.01138  -0.0914   0.9164   0.0176
  -5.750  -0.2193   0.01746   0.01019  -0.0911   0.9103   0.0187
  -5.500  -0.1924   0.01653   0.00908  -0.0910   0.9048   0.0200
  -5.250  -0.1651   0.01565   0.00811  -0.0910   0.9001   0.0222
  -5.000  -0.1397   0.01510   0.00751  -0.0907   0.8934   0.0258
  -4.750  -0.1122   0.01451   0.00686  -0.0907   0.8884   0.0321
  -4.500  -0.0859   0.01420   0.00649  -0.0905   0.8822   0.0408
  -4.250  -0.0588   0.01390   0.00614  -0.0904   0.8764   0.0496
  -4.000  -0.0313   0.01359   0.00582  -0.0904   0.8713   0.0605
  -3.750  -0.0054   0.01325   0.00543  -0.0901   0.8647   0.0678
  -3.500   0.0223   0.01292   0.00504  -0.0901   0.8596   0.0778
  -3.250   0.0484   0.01259   0.00471  -0.0899   0.8532   0.0912
  -3.000   0.0753   0.01224   0.00440  -0.0898   0.8474   0.1154
  -2.750   0.1018   0.01178   0.00413  -0.0897   0.8418   0.1741
  -2.500   0.1268   0.01116   0.00390  -0.0896   0.8351   0.2918
  -2.250   0.1513   0.01046   0.00385  -0.0893   0.8299   0.4875
  -2.000   0.1765   0.01035   0.00389  -0.0887   0.8224   0.5577
  -1.750   0.2039   0.01028   0.00382  -0.0883   0.8166   0.5943
  -1.500   0.2301   0.01024   0.00379  -0.0878   0.8089   0.6213
  -1.250   0.2565   0.01017   0.00375  -0.0872   0.8024   0.6583
  -1.000   0.2818   0.01010   0.00376  -0.0864   0.7945   0.6897
  -0.750   0.3088   0.01004   0.00368  -0.0860   0.7880   0.7078
  -0.500   0.3353   0.01000   0.00365  -0.0856   0.7803   0.7207
  -0.250   0.3630   0.00997   0.00357  -0.0853   0.7739   0.7314
   0.000   0.3896   0.00995   0.00357  -0.0850   0.7662   0.7426
   0.250   0.4167   0.00991   0.00351  -0.0846   0.7585   0.7550
   0.500   0.4425   0.00989   0.00349  -0.0840   0.7472   0.7692
   0.750   0.4682   0.00986   0.00347  -0.0833   0.7353   0.7856
   1.000   0.4940   0.00986   0.00347  -0.0826   0.7249   0.8041
   1.250   0.5200   0.00986   0.00346  -0.0820   0.7161   0.8250
   1.500   0.5455   0.00987   0.00350  -0.0814   0.7057   0.8474
   1.750   0.5711   0.00987   0.00351  -0.0807   0.6955   0.8689
   2.000   0.5971   0.00986   0.00351  -0.0802   0.6846   0.8912
   2.250   0.6258   0.00983   0.00349  -0.0801   0.6719   0.9173
   2.500   0.6622   0.00982   0.00349  -0.0818   0.6560   0.9644
   2.750   0.6913   0.00992   0.00354  -0.0822   0.6394   1.0000
   3.000   0.7175   0.01005   0.00362  -0.0819   0.6226   1.0000
   3.250   0.7434   0.01019   0.00370  -0.0815   0.6044   1.0000
   3.500   0.7690   0.01036   0.00380  -0.0811   0.5842   1.0000
   3.750   0.7939   0.01056   0.00394  -0.0806   0.5612   1.0000
   4.000   0.8183   0.01080   0.00408  -0.0799   0.5346   1.0000
   4.250   0.8418   0.01110   0.00425  -0.0792   0.5052   1.0000
   4.500   0.8645   0.01145   0.00447  -0.0783   0.4744   1.0000
   4.750   0.8868   0.01184   0.00475  -0.0773   0.4433   1.0000
   5.000   0.9087   0.01226   0.00504  -0.0764   0.4133   1.0000
   5.250   0.9304   0.01271   0.00538  -0.0754   0.3839   1.0000
   5.500   0.9518   0.01318   0.00574  -0.0745   0.3558   1.0000
   5.750   0.9729   0.01366   0.00614  -0.0735   0.3289   1.0000
   6.000   0.9940   0.01416   0.00655  -0.0725   0.3051   1.0000
   6.250   1.0148   0.01466   0.00699  -0.0715   0.2837   1.0000
   6.500   1.0356   0.01518   0.00745  -0.0705   0.2635   1.0000
   6.750   1.0558   0.01571   0.00793  -0.0695   0.2441   1.0000
   7.000   1.0763   0.01623   0.00843  -0.0684   0.2243   1.0000
   7.250   1.0959   0.01678   0.00893  -0.0673   0.2054   1.0000
   7.500   1.1150   0.01736   0.00947  -0.0661   0.1870   1.0000
   7.750   1.1334   0.01797   0.01002  -0.0649   0.1670   1.0000
   8.000   1.1503   0.01867   0.01063  -0.0635   0.1471   1.0000
   8.250   1.1680   0.01931   0.01127  -0.0621   0.1298   1.0000
   8.500   1.1837   0.02001   0.01191  -0.0605   0.1117   1.0000
   9.000   1.2113   0.02157   0.01336  -0.0568   0.0803   1.0000
   9.250   1.2243   0.02243   0.01418  -0.0549   0.0667   1.0000
   9.500   1.2364   0.02336   0.01507  -0.0530   0.0545   1.0000
   9.750   1.2490   0.02426   0.01599  -0.0512   0.0471   1.0000
  10.000   1.2623   0.02513   0.01693  -0.0495   0.0417   1.0000
  10.250   1.2737   0.02614   0.01801  -0.0477   0.0364   1.0000
  10.500   1.2849   0.02719   0.01913  -0.0460   0.0299   1.0000
  10.750   1.2932   0.02850   0.02043  -0.0441   0.0215   1.0000
  11.000   1.3004   0.02993   0.02187  -0.0423   0.0150   1.0000
  11.250   1.3065   0.03149   0.02347  -0.0405   0.0105   1.0000
  11.500   1.3125   0.03308   0.02514  -0.0388   0.0087   1.0000
  11.750   1.3189   0.03469   0.02687  -0.0372   0.0078   1.0000
  12.000   1.3236   0.03650   0.02881  -0.0358   0.0070   1.0000
  12.250   1.3274   0.03844   0.03088  -0.0344   0.0066   1.0000
  12.500   1.3301   0.04056   0.03314  -0.0332   0.0063   1.0000
  12.750   1.3313   0.04289   0.03562  -0.0321   0.0061   1.0000
  13.000   1.3307   0.04551   0.03843  -0.0313   0.0059   1.0000
  13.250   1.3302   0.04821   0.04131  -0.0306   0.0058   1.0000
  13.500   1.3278   0.05123   0.04451  -0.0302   0.0056   1.0000
  13.750   1.3237   0.05459   0.04805  -0.0301   0.0055   1.0000
  14.000   1.3188   0.05820   0.05184  -0.0304   0.0055   1.0000
  14.250   1.3124   0.06221   0.05603  -0.0310   0.0054   1.0000
  14.500   1.3054   0.06652   0.06052  -0.0319   0.0054   1.0000
  14.750   1.2969   0.07130   0.06548  -0.0333   0.0053   1.0000
  15.000   1.2869   0.07658   0.07094  -0.0352   0.0053   1.0000
  15.250   1.2761   0.08227   0.07681  -0.0375   0.0052   1.0000
  15.500   1.2650   0.08828   0.08300  -0.0402   0.0052   1.0000
  15.750   1.2525   0.09481   0.08971  -0.0433   0.0052   1.0000
  16.000   1.2404   0.10148   0.09655  -0.0466   0.0052   1.0000
  16.250   1.2267   0.10870   0.10394  -0.0503   0.0052   1.0000
  16.500   1.2136   0.11599   0.11139  -0.0542   0.0052   1.0000
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