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HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 0/10 AIRFOIL (hq010-il)
Reynolds number: 50,000
Max Cl/Cd: 27.3 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq010-il-50000-n5.txt
Download as CSV file: xf-hq010-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7094   0.09429   0.08749  -0.0095   1.0000   0.0531
 -10.750  -0.7244   0.08695   0.08016  -0.0145   1.0000   0.0526
 -10.500  -0.7431   0.08022   0.07341  -0.0190   1.0000   0.0521
 -10.250  -0.7636   0.07447   0.06759  -0.0222   1.0000   0.0517
 -10.000  -0.7835   0.06970   0.06271  -0.0235   1.0000   0.0513
  -9.750  -0.8022   0.06557   0.05841  -0.0232   1.0000   0.0513
  -9.500  -0.8153   0.06130   0.05387  -0.0226   1.0000   0.0515
  -9.250  -0.8228   0.05706   0.04927  -0.0217   1.0000   0.0518
  -9.000  -0.8252   0.05291   0.04468  -0.0205   1.0000   0.0525
  -8.750  -0.8220   0.04901   0.04024  -0.0192   1.0000   0.0533
  -8.500  -0.8136   0.04543   0.03606  -0.0179   1.0000   0.0545
  -8.250  -0.7988   0.04251   0.03302  -0.0171   1.0000   0.0569
  -8.000  -0.7824   0.04045   0.03068  -0.0163   1.0000   0.0614
  -7.750  -0.7644   0.03798   0.02773  -0.0153   1.0000   0.0654
  -7.500  -0.7423   0.03544   0.02480  -0.0144   1.0000   0.0682
  -7.250  -0.7194   0.03337   0.02269  -0.0138   1.0000   0.0719
  -7.000  -0.6958   0.03162   0.02072  -0.0130   1.0000   0.0776
  -6.750  -0.6741   0.03009   0.01915  -0.0122   1.0000   0.0863
  -6.500  -0.6514   0.02860   0.01751  -0.0113   1.0000   0.0958
  -6.250  -0.6301   0.02716   0.01599  -0.0101   1.0000   0.1063
  -6.000  -0.6116   0.02575   0.01463  -0.0090   1.0000   0.1233
  -5.750  -0.5939   0.02440   0.01348  -0.0078   1.0000   0.1496
  -5.500  -0.5768   0.02308   0.01240  -0.0065   1.0000   0.1918
  -5.250  -0.5615   0.02168   0.01137  -0.0051   1.0000   0.2575
  -5.000  -0.5477   0.02040   0.01063  -0.0032   1.0000   0.3373
  -4.750  -0.5328   0.01952   0.01023  -0.0009   1.0000   0.4330
  -4.500  -0.5168   0.01910   0.01020   0.0020   1.0000   0.5152
  -4.250  -0.5000   0.01900   0.01021   0.0050   1.0000   0.5833
  -4.000  -0.4841   0.01908   0.01033   0.0083   1.0000   0.6410
  -3.750  -0.4683   0.01919   0.01042   0.0116   1.0000   0.6858
  -3.500  -0.4516   0.01921   0.01036   0.0145   1.0000   0.7179
  -3.250  -0.4329   0.01917   0.01020   0.0168   1.0000   0.7409
  -3.000  -0.4149   0.01908   0.01000   0.0189   1.0000   0.7620
  -2.750  -0.3968   0.01900   0.00977   0.0210   1.0000   0.7820
  -2.500  -0.3798   0.01889   0.00955   0.0231   1.0000   0.8018
  -2.250  -0.3602   0.01885   0.00942   0.0248   1.0000   0.8208
  -2.000  -0.3408   0.01886   0.00936   0.0267   1.0000   0.8448
  -1.750  -0.3162   0.01896   0.00939   0.0278   1.0000   0.8710
  -1.500  -0.2809   0.01913   0.00944   0.0267   1.0000   0.8943
  -1.250  -0.2473   0.01918   0.00939   0.0252   1.0000   0.9131
  -1.000  -0.2121   0.01918   0.00930   0.0230   1.0000   0.9276
  -0.750  -0.1639   0.01923   0.00924   0.0182   0.9930   0.9386
  -0.500  -0.1092   0.01929   0.00922   0.0121   0.9844   0.9474
  -0.250  -0.0555   0.01933   0.00920   0.0062   0.9751   0.9569
   0.000   0.0000   0.01936   0.00921   0.0000   0.9662   0.9662
   0.250   0.0555   0.01933   0.00920  -0.0062   0.9569   0.9751
   0.500   0.1092   0.01929   0.00922  -0.0121   0.9474   0.9844
   0.750   0.1639   0.01923   0.00923  -0.0182   0.9386   0.9931
   1.000   0.2122   0.01917   0.00930  -0.0230   0.9275   1.0000
   1.250   0.2473   0.01918   0.00939  -0.0252   0.9131   1.0000
   1.500   0.2809   0.01913   0.00944  -0.0267   0.8944   1.0000
   1.750   0.3161   0.01896   0.00940  -0.0277   0.8710   1.0000
   2.000   0.3407   0.01886   0.00936  -0.0267   0.8449   1.0000
   2.250   0.3602   0.01885   0.00942  -0.0248   0.8209   1.0000
   2.500   0.3798   0.01889   0.00956  -0.0231   0.8019   1.0000
   2.750   0.3968   0.01900   0.00977  -0.0210   0.7820   1.0000
   3.000   0.4149   0.01908   0.00999  -0.0189   0.7620   1.0000
   3.250   0.4329   0.01917   0.01020  -0.0168   0.7410   1.0000
   3.500   0.4515   0.01921   0.01036  -0.0145   0.7179   1.0000
   3.750   0.4683   0.01919   0.01042  -0.0116   0.6857   1.0000
   4.000   0.4841   0.01908   0.01033  -0.0083   0.6410   1.0000
   4.250   0.5000   0.01900   0.01021  -0.0050   0.5834   1.0000
   4.500   0.5168   0.01910   0.01020  -0.0020   0.5152   1.0000
   4.750   0.5328   0.01952   0.01023   0.0009   0.4332   1.0000
   5.000   0.5477   0.02039   0.01063   0.0032   0.3375   1.0000
   5.250   0.5615   0.02168   0.01137   0.0051   0.2575   1.0000
   5.500   0.5768   0.02308   0.01240   0.0065   0.1919   1.0000
   5.750   0.5939   0.02440   0.01348   0.0078   0.1495   1.0000
   6.000   0.6115   0.02576   0.01463   0.0090   0.1232   1.0000
   6.250   0.6301   0.02716   0.01599   0.0101   0.1063   1.0000
   6.500   0.6514   0.02861   0.01751   0.0113   0.0957   1.0000
   6.750   0.6741   0.03009   0.01915   0.0122   0.0862   1.0000
   7.000   0.6957   0.03162   0.02072   0.0130   0.0775   1.0000
   7.250   0.7193   0.03338   0.02270   0.0138   0.0718   1.0000
   7.500   0.7423   0.03545   0.02481   0.0144   0.0681   1.0000
   7.750   0.7643   0.03798   0.02774   0.0153   0.0654   1.0000
   8.000   0.7824   0.04046   0.03069   0.0163   0.0614   1.0000
   8.250   0.7987   0.04252   0.03302   0.0171   0.0569   1.0000
   8.500   0.8136   0.04541   0.03604   0.0179   0.0545   1.0000
   8.750   0.8221   0.04899   0.04023   0.0192   0.0534   1.0000
   9.000   0.8250   0.05294   0.04471   0.0205   0.0524   1.0000
   9.250   0.8230   0.05705   0.04926   0.0217   0.0519   1.0000
   9.500   0.8154   0.06129   0.05386   0.0226   0.0515   1.0000
   9.750   0.8023   0.06556   0.05840   0.0232   0.0513   1.0000
  10.000   0.7836   0.06972   0.06274   0.0235   0.0513   1.0000
  10.250   0.7632   0.07453   0.06765   0.0221   0.0516   1.0000
  10.500   0.7431   0.08027   0.07346   0.0189   0.0521   1.0000
  10.750   0.7249   0.08695   0.08016   0.0144   0.0526   1.0000
  11.000   0.7095   0.09439   0.08759   0.0094   0.0531   1.0000
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