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HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 0/10 AIRFOIL (hq010-il)
Reynolds number: 200,000
Max Cl/Cd: 50.06 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq010-il-200000.txt
Download as CSV file: xf-hq010-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 0/10 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7335   0.08061   0.07725  -0.0133   1.0000   0.0277
 -10.750  -0.8143   0.06107   0.05725  -0.0259   1.0000   0.0199
 -10.500  -0.8353   0.05648   0.05249  -0.0271   1.0000   0.0198
 -10.250  -0.8563   0.05250   0.04832  -0.0262   1.0000   0.0196
 -10.000  -0.8705   0.04973   0.04528  -0.0237   1.0000   0.0204
  -9.750  -0.8767   0.04702   0.04223  -0.0217   1.0000   0.0210
  -9.250  -0.8882   0.03848   0.03304  -0.0180   1.0000   0.0234
  -9.000  -0.8742   0.03721   0.03169  -0.0170   1.0000   0.0259
  -8.750  -0.8648   0.03415   0.02817  -0.0151   1.0000   0.0286
  -8.500  -0.8502   0.03257   0.02610  -0.0133   1.0000   0.0312
  -8.250  -0.8368   0.02961   0.02305  -0.0126   1.0000   0.0354
  -8.000  -0.8160   0.02926   0.02255  -0.0118   1.0000   0.0403
  -7.750  -0.7954   0.02766   0.02059  -0.0106   1.0000   0.0418
  -7.500  -0.7754   0.02478   0.01735  -0.0097   1.0000   0.0438
  -7.250  -0.7531   0.02300   0.01552  -0.0091   1.0000   0.0463
  -7.000  -0.7296   0.02158   0.01398  -0.0083   1.0000   0.0481
  -6.750  -0.7061   0.02032   0.01260  -0.0075   1.0000   0.0504
  -6.500  -0.6827   0.01923   0.01140  -0.0066   1.0000   0.0531
  -6.250  -0.6610   0.01789   0.01002  -0.0056   1.0000   0.0562
  -6.000  -0.6401   0.01692   0.00910  -0.0046   1.0000   0.0621
  -5.750  -0.6191   0.01604   0.00815  -0.0034   1.0000   0.0694
  -5.500  -0.5989   0.01519   0.00733  -0.0022   1.0000   0.0797
  -5.250  -0.5810   0.01416   0.00641  -0.0007   1.0000   0.0971
  -5.000  -0.5646   0.01312   0.00563   0.0010   1.0000   0.1333
  -4.750  -0.5500   0.01210   0.00514   0.0027   1.0000   0.2254
  -4.500  -0.5354   0.01137   0.00475   0.0046   1.0000   0.2938
  -4.250  -0.5232   0.01069   0.00450   0.0069   1.0000   0.3776
  -4.000  -0.5107   0.01020   0.00434   0.0092   1.0000   0.4626
  -3.750  -0.4950   0.00990   0.00437   0.0111   0.9993   0.5404
  -3.500  -0.4564   0.00980   0.00447   0.0088   0.9917   0.6127
  -3.250  -0.4175   0.00983   0.00453   0.0066   0.9841   0.6572
  -3.000  -0.3793   0.00988   0.00457   0.0046   0.9769   0.6905
  -2.750  -0.3402   0.00995   0.00464   0.0025   0.9703   0.7186
  -2.500  -0.3016   0.01004   0.00474   0.0007   0.9636   0.7450
  -2.250  -0.2617   0.01007   0.00477  -0.0014   0.9563   0.7624
  -2.000  -0.2249   0.01004   0.00469  -0.0030   0.9471   0.7751
  -1.750  -0.1876   0.01003   0.00464  -0.0047   0.9399   0.7875
  -1.500  -0.1579   0.01003   0.00464  -0.0047   0.9296   0.7992
  -1.250  -0.1287   0.01004   0.00463  -0.0046   0.9198   0.8107
  -1.000  -0.1000   0.01003   0.00461  -0.0043   0.9106   0.8218
  -0.750  -0.0740   0.01003   0.00461  -0.0035   0.9001   0.8336
  -0.500  -0.0495   0.01004   0.00462  -0.0022   0.8889   0.8462
  -0.250  -0.0250   0.01003   0.00461  -0.0011   0.8781   0.8579
   0.000   0.0000   0.01003   0.00459   0.0000   0.8681   0.8682
   0.250   0.0250   0.01003   0.00461   0.0011   0.8579   0.8781
   0.500   0.0495   0.01004   0.00462   0.0023   0.8461   0.8889
   0.750   0.0740   0.01003   0.00461   0.0035   0.8337   0.9001
   1.000   0.1000   0.01003   0.00461   0.0043   0.8218   0.9105
   1.250   0.1287   0.01004   0.00463   0.0046   0.8107   0.9199
   1.500   0.1580   0.01003   0.00464   0.0047   0.7993   0.9296
   1.750   0.1876   0.01003   0.00464   0.0046   0.7875   0.9399
   2.000   0.2250   0.01004   0.00470   0.0030   0.7751   0.9471
   2.250   0.2618   0.01007   0.00477   0.0014   0.7625   0.9563
   2.500   0.3016   0.01004   0.00474  -0.0006   0.7448   0.9636
   2.750   0.3401   0.00995   0.00464  -0.0025   0.7185   0.9703
   3.000   0.3793   0.00988   0.00457  -0.0046   0.6906   0.9769
   3.250   0.4175   0.00983   0.00453  -0.0066   0.6573   0.9841
   3.500   0.4564   0.00980   0.00446  -0.0088   0.6128   0.9917
   3.750   0.4950   0.00990   0.00437  -0.0111   0.5405   0.9994
   4.000   0.5106   0.01020   0.00434  -0.0092   0.4625   1.0000
   4.250   0.5231   0.01070   0.00450  -0.0069   0.3766   1.0000
   4.500   0.5354   0.01137   0.00475  -0.0046   0.2938   1.0000
   4.750   0.5500   0.01210   0.00514  -0.0027   0.2253   1.0000
   5.000   0.5646   0.01312   0.00563  -0.0010   0.1336   1.0000
   5.250   0.5810   0.01417   0.00641   0.0007   0.0970   1.0000
   5.500   0.5989   0.01519   0.00733   0.0022   0.0798   1.0000
   5.750   0.6191   0.01605   0.00816   0.0035   0.0693   1.0000
   6.000   0.6402   0.01690   0.00908   0.0046   0.0617   1.0000
   6.250   0.6610   0.01790   0.01003   0.0056   0.0562   1.0000
   6.500   0.6827   0.01922   0.01139   0.0067   0.0530   1.0000
   6.750   0.7061   0.02032   0.01260   0.0075   0.0504   1.0000
   7.000   0.7296   0.02158   0.01398   0.0083   0.0481   1.0000
   7.250   0.7530   0.02300   0.01552   0.0091   0.0463   1.0000
   7.500   0.7753   0.02482   0.01738   0.0097   0.0437   1.0000
   7.750   0.7954   0.02768   0.02060   0.0106   0.0419   1.0000
   8.000   0.8159   0.02935   0.02264   0.0118   0.0404   1.0000
   8.250   0.8365   0.02978   0.02324   0.0126   0.0356   1.0000
   8.500   0.8496   0.03275   0.02629   0.0133   0.0311   1.0000
   8.750   0.8649   0.03411   0.02814   0.0151   0.0285   1.0000
   9.000   0.8742   0.03718   0.03166   0.0170   0.0258   1.0000
   9.250   0.8905   0.03780   0.03225   0.0177   0.0230   1.0000
   9.500   0.8915   0.04185   0.03658   0.0193   0.0219   1.0000
  10.000   0.8691   0.05003   0.04558   0.0237   0.0206   1.0000
  10.250   0.8553   0.05275   0.04856   0.0262   0.0199   1.0000
  10.500   0.8356   0.05653   0.05253   0.0270   0.0200   1.0000
  10.750   0.8137   0.06140   0.05754   0.0259   0.0205   1.0000
  11.000   0.7882   0.06795   0.06419   0.0230   0.0211   1.0000
  11.250   0.7125   0.09159   0.08823   0.0055   0.0292   1.0000
  11.500   0.6975   0.10038   0.09697   0.0008   0.0302   1.0000
  11.750   0.6585   0.12133   0.11780  -0.0103   0.0514   1.0000
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