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HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/8 AIRFOIL (hq258-il)
Reynolds number: 50,000
Max Cl/Cd: 40.49 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq258-il-50000-n5.txt
Download as CSV file: xf-hq258-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4265   0.11570   0.10867  -0.0215   1.0000   0.0896
  -9.250  -0.4324   0.11372   0.10679  -0.0247   1.0000   0.0926
  -9.000  -0.4410   0.11188   0.10509  -0.0282   1.0000   0.0934
  -8.750  -0.4240   0.10618   0.09939  -0.0261   1.0000   0.0954
  -8.500  -0.4164   0.10255   0.09580  -0.0260   1.0000   0.0979
  -8.250  -0.4138   0.09935   0.09266  -0.0267   1.0000   0.1005
  -7.750  -0.3351   0.07886   0.07275  -0.0334   1.0000   0.0626
  -7.500  -0.3451   0.07465   0.06862  -0.0355   1.0000   0.0515
  -7.250  -0.3454   0.07107   0.06512  -0.0345   1.0000   0.0486
  -7.000  -0.4151   0.07940   0.07307  -0.0393   1.0000   0.0514
  -6.750  -0.4119   0.07578   0.06951  -0.0388   1.0000   0.0478
  -6.500  -0.4105   0.07160   0.06536  -0.0409   1.0000   0.0449
  -6.250  -0.4060   0.06639   0.05990  -0.0460   1.0000   0.0395
  -6.000  -0.4009   0.06293   0.05646  -0.0454   1.0000   0.0385
  -5.750  -0.3946   0.05921   0.05267  -0.0458   1.0000   0.0375
  -5.500  -0.3860   0.05552   0.04885  -0.0463   1.0000   0.0367
  -5.250  -0.3747   0.05174   0.04486  -0.0469   1.0000   0.0359
  -5.000  -0.3605   0.04797   0.04081  -0.0476   1.0000   0.0351
  -4.750  -0.3435   0.04430   0.03679  -0.0481   1.0000   0.0346
  -4.500  -0.3240   0.04077   0.03283  -0.0485   1.0000   0.0343
  -4.250  -0.3023   0.03752   0.02911  -0.0487   1.0000   0.0343
  -4.000  -0.2790   0.03455   0.02564  -0.0487   1.0000   0.0347
  -3.750  -0.2546   0.03206   0.02261  -0.0484   1.0000   0.0368
  -3.500  -0.2293   0.02998   0.01994  -0.0479   1.0000   0.0408
  -3.250  -0.2065   0.02807   0.01786  -0.0475   1.0000   0.0455
  -3.000  -0.1819   0.02631   0.01577  -0.0465   1.0000   0.0483
  -2.750  -0.1579   0.02486   0.01386  -0.0451   1.0000   0.0524
  -2.500  -0.1351   0.02355   0.01247  -0.0441   1.0000   0.0620
  -2.250  -0.1109   0.02250   0.01130  -0.0436   1.0000   0.0831
  -2.000  -0.0846   0.02130   0.01015  -0.0439   1.0000   0.1248
  -1.750  -0.0570   0.01851   0.00945  -0.0448   1.0000   0.5260
  -1.500  -0.0524   0.01796   0.00955  -0.0385   1.0000   0.7814
  -1.250  -0.0164   0.01751   0.00903  -0.0394   0.9915   1.0000
  -1.000   0.0227   0.01784   0.00883  -0.0424   0.9846   1.0000
  -0.750   0.0600   0.01814   0.00865  -0.0450   0.9768   1.0000
  -0.500   0.0969   0.01847   0.00863  -0.0475   0.9689   1.0000
  -0.250   0.1355   0.01882   0.00869  -0.0503   0.9614   1.0000
   0.000   0.1699   0.01912   0.00876  -0.0522   0.9523   1.0000
   0.250   0.2067   0.01944   0.00883  -0.0545   0.9437   1.0000
   0.500   0.2445   0.01975   0.00900  -0.0570   0.9351   1.0000
   0.750   0.2784   0.02003   0.00917  -0.0586   0.9248   1.0000
   1.000   0.3138   0.02031   0.00937  -0.0605   0.9147   1.0000
   1.250   0.3520   0.02056   0.00957  -0.0627   0.9052   1.0000
   1.500   0.3891   0.02079   0.00978  -0.0647   0.8950   1.0000
   1.750   0.4231   0.02101   0.01001  -0.0661   0.8834   1.0000
   2.000   0.4571   0.02120   0.01028  -0.0673   0.8716   1.0000
   2.250   0.4919   0.02130   0.01044  -0.0684   0.8585   1.0000
   2.500   0.5274   0.02129   0.01050  -0.0694   0.8438   1.0000
   2.750   0.5628   0.02120   0.01052  -0.0701   0.8283   1.0000
   3.000   0.5949   0.02114   0.01057  -0.0703   0.8117   1.0000
   3.250   0.6235   0.02114   0.01080  -0.0698   0.7933   1.0000
   3.500   0.6550   0.02101   0.01083  -0.0696   0.7752   1.0000
   3.750   0.6828   0.02094   0.01092  -0.0687   0.7538   1.0000
   4.000   0.7123   0.02077   0.01092  -0.0680   0.7314   1.0000
   4.250   0.7396   0.02066   0.01098  -0.0668   0.7050   1.0000
   4.500   0.7652   0.02063   0.01125  -0.0654   0.6738   1.0000
   4.750   0.7919   0.02056   0.01132  -0.0640   0.6382   1.0000
   5.000   0.8161   0.02064   0.01151  -0.0624   0.5940   1.0000
   5.250   0.8400   0.02084   0.01170  -0.0606   0.5425   1.0000
   5.500   0.8620   0.02129   0.01206  -0.0588   0.4849   1.0000
   5.750   0.8821   0.02203   0.01264  -0.0569   0.4274   1.0000
   6.000   0.9008   0.02299   0.01345  -0.0552   0.3742   1.0000
   6.250   0.9189   0.02408   0.01444  -0.0536   0.3269   1.0000
   6.500   0.9370   0.02526   0.01576  -0.0521   0.2849   1.0000
   6.750   0.9548   0.02653   0.01705  -0.0506   0.2466   1.0000
   7.000   0.9686   0.02789   0.01840  -0.0489   0.1950   1.0000
   7.250   0.9750   0.02999   0.01965  -0.0473   0.0897   1.0000
   7.500   0.9858   0.03293   0.02215  -0.0454   0.0459   1.0000
   7.750   0.9993   0.03524   0.02453  -0.0437   0.0341   1.0000
   8.000   1.0107   0.03765   0.02700  -0.0421   0.0281   1.0000
   8.250   1.0257   0.03992   0.02964  -0.0403   0.0259   1.0000
   8.500   1.0413   0.04253   0.03261  -0.0386   0.0241   1.0000
   8.750   1.0570   0.04542   0.03586  -0.0370   0.0228   1.0000
   9.000   1.0705   0.04862   0.03946  -0.0355   0.0218   1.0000
   9.250   1.0800   0.05205   0.04328  -0.0339   0.0211   1.0000
   9.500   1.0845   0.05565   0.04728  -0.0322   0.0207   1.0000
   9.750   1.0826   0.05930   0.05129  -0.0302   0.0204   1.0000
  10.000   1.0759   0.06302   0.05535  -0.0282   0.0203   1.0000
  10.250   1.0652   0.06698   0.05962  -0.0269   0.0203   1.0000
  10.500   1.0514   0.07135   0.06427  -0.0264   0.0204   1.0000
  10.750   1.0353   0.07626   0.06944  -0.0271   0.0205   1.0000
  11.000   1.0174   0.08192   0.07532  -0.0291   0.0207   1.0000
  11.250   0.9982   0.08849   0.08208  -0.0325   0.0209   1.0000
  11.500   0.9778   0.09639   0.09014  -0.0376   0.0213   1.0000
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