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HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/9 AIRFOIL (hq209-il)
Reynolds number: 100,000
Max Cl/Cd: 55.18 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq209-il-100000.txt
Download as CSV file: xf-hq209-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/9 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4477   0.09892   0.09405  -0.0241   1.0000   0.0896
  -8.750  -0.4572   0.09577   0.09100  -0.0283   1.0000   0.0930
  -8.500  -0.4768   0.09262   0.08799  -0.0344   1.0000   0.0940
  -8.250  -0.4548   0.08791   0.08326  -0.0298   1.0000   0.0975
  -8.000  -0.4501   0.08483   0.08023  -0.0296   1.0000   0.1014
  -7.750  -0.4594   0.08160   0.07710  -0.0318   1.0000   0.1048
  -7.500  -0.4867   0.07705   0.07256  -0.0422   1.0000   0.1075
  -7.250  -0.4771   0.07271   0.06833  -0.0395   1.0000   0.1103
  -7.000  -0.4692   0.07002   0.06564  -0.0375   1.0000   0.1147
  -6.750  -0.4938   0.06658   0.06192  -0.0442   1.0000   0.1220
  -6.500  -0.4764   0.06269   0.05828  -0.0398   1.0000   0.1256
  -6.250  -0.4860   0.05990   0.05520  -0.0419   1.0000   0.1362
  -6.000  -0.4750   0.05666   0.05218  -0.0385   1.0000   0.1401
  -5.750  -0.4746   0.05369   0.04906  -0.0384   1.0000   0.1517
  -5.500  -0.4698   0.05102   0.04630  -0.0374   1.0000   0.1650
  -5.250  -0.4623   0.04859   0.04391  -0.0354   1.0000   0.1805
  -5.000  -0.4172   0.02437   0.01811  -0.0370   1.0000   0.0666
  -4.750  -0.4008   0.02064   0.01411  -0.0365   1.0000   0.0654
  -4.500  -0.3815   0.01724   0.01036  -0.0358   1.0000   0.0634
  -4.250  -0.3591   0.01397   0.00660  -0.0351   1.0000   0.0605
  -4.000  -0.3353   0.01139   0.00355  -0.0343   1.0000   0.0600
  -3.750  -0.3115   0.00943   0.00127  -0.0334   1.0000   0.0620
  -3.500  -0.2895   0.02108   0.01211  -0.0337   1.0000   0.0700
  -3.250  -0.2662   0.01991   0.01083  -0.0327   1.0000   0.0799
  -3.000  -0.2441   0.01853   0.00960  -0.0319   1.0000   0.0996
  -2.750  -0.2223   0.01749   0.00871  -0.0311   1.0000   0.1334
  -2.500  -0.2001   0.01608   0.00786  -0.0306   1.0000   0.2120
  -2.250  -0.1913   0.01424   0.00821  -0.0264   1.0000   0.6928
  -2.000  -0.1808   0.01434   0.00841  -0.0221   1.0000   0.7755
  -1.750  -0.1704   0.01435   0.00846  -0.0181   1.0000   0.8340
  -1.500  -0.1565   0.01425   0.00842  -0.0147   1.0000   0.8982
  -1.250  -0.0957   0.01434   0.00829  -0.0218   0.9947   1.0000
  -1.000  -0.0511   0.01468   0.00835  -0.0264   0.9867   1.0000
  -0.750  -0.0063   0.01508   0.00848  -0.0309   0.9792   1.0000
  -0.500   0.0377   0.01545   0.00865  -0.0351   0.9710   1.0000
  -0.250   0.0781   0.01577   0.00880  -0.0384   0.9620   1.0000
   0.000   0.1254   0.01615   0.00902  -0.0429   0.9547   1.0000
   0.250   0.1620   0.01640   0.00917  -0.0453   0.9445   1.0000
   0.500   0.2005   0.01667   0.00936  -0.0479   0.9350   1.0000
   0.750   0.2480   0.01692   0.00955  -0.0521   0.9277   1.0000
   1.000   0.2866   0.01706   0.00966  -0.0544   0.9160   1.0000
   1.250   0.3337   0.01700   0.00959  -0.0579   0.9034   1.0000
   1.500   0.3852   0.01675   0.00936  -0.0618   0.8905   1.0000
   1.750   0.4275   0.01658   0.00924  -0.0640   0.8784   1.0000
   2.000   0.4665   0.01647   0.00916  -0.0656   0.8676   1.0000
   2.250   0.5066   0.01625   0.00900  -0.0672   0.8573   1.0000
   2.500   0.5401   0.01610   0.00894  -0.0675   0.8448   1.0000
   2.750   0.5707   0.01597   0.00887  -0.0672   0.8310   1.0000
   3.000   0.5993   0.01583   0.00879  -0.0665   0.8158   1.0000
   3.250   0.6252   0.01574   0.00878  -0.0653   0.7984   1.0000
   3.500   0.6527   0.01552   0.00868  -0.0642   0.7805   1.0000
   3.750   0.6813   0.01521   0.00843  -0.0630   0.7623   1.0000
   4.000   0.7061   0.01503   0.00833  -0.0614   0.7385   1.0000
   4.250   0.7315   0.01480   0.00816  -0.0597   0.7118   1.0000
   4.500   0.7569   0.01457   0.00797  -0.0580   0.6796   1.0000
   4.750   0.7799   0.01447   0.00783  -0.0559   0.6365   1.0000
   5.000   0.8013   0.01454   0.00777  -0.0537   0.5792   1.0000
   5.250   0.8211   0.01488   0.00785  -0.0515   0.5120   1.0000
   5.500   0.8400   0.01553   0.00815  -0.0495   0.4456   1.0000
   5.750   0.8588   0.01632   0.00865  -0.0479   0.3884   1.0000
   6.000   0.8779   0.01715   0.00934  -0.0464   0.3375   1.0000
   6.250   0.8958   0.01811   0.01009  -0.0449   0.2868   1.0000
   6.500   0.9103   0.01943   0.01106  -0.0430   0.2221   1.0000
   6.750   0.9245   0.02100   0.01223  -0.0410   0.1589   1.0000
   7.000   0.9416   0.02261   0.01358  -0.0394   0.1306   1.0000
   7.250   0.9614   0.02418   0.01505  -0.0381   0.1131   1.0000
   7.500   0.9829   0.02582   0.01665  -0.0372   0.1005   1.0000
   7.750   1.0070   0.02768   0.01857  -0.0365   0.0913   1.0000
   8.000   1.0302   0.02967   0.02079  -0.0356   0.0816   1.0000
   8.250   1.0454   0.03096   0.02209  -0.0344   0.0669   1.0000
   8.500   1.0625   0.03330   0.02458  -0.0331   0.0545   1.0000
   8.750   1.0795   0.03653   0.02817  -0.0314   0.0458   1.0000
   9.000   1.0939   0.04022   0.03192  -0.0304   0.0400   1.0000
   9.250   1.1046   0.04315   0.03547  -0.0281   0.0380   1.0000
   9.500   1.1110   0.04693   0.03979  -0.0257   0.0370   1.0000
   9.750   1.1115   0.05100   0.04436  -0.0231   0.0365   1.0000
  10.000   1.1071   0.05510   0.04890  -0.0206   0.0365   1.0000
  10.250   1.0971   0.05919   0.05336  -0.0180   0.0367   1.0000
  10.500   1.0815   0.06293   0.05738  -0.0151   0.0370   1.0000
  10.750   1.0627   0.06678   0.06147  -0.0131   0.0373   1.0000
  11.000   1.0425   0.07107   0.06596  -0.0123   0.0376   1.0000
  11.250   1.0221   0.07585   0.07092  -0.0129   0.0380   1.0000
  11.500   1.0011   0.08134   0.07657  -0.0149   0.0384   1.0000
  11.750   0.9787   0.08782   0.08318  -0.0183   0.0387   1.0000
  12.000   0.9588   0.09501   0.09045  -0.0227   0.0393   1.0000
  12.250   0.9419   0.10274   0.09823  -0.0273   0.0398   1.0000
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