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HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/8 AIRFOIL (hq208-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.75 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq208-il-1000000.txt
Download as CSV file: xf-hq208-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3890   0.09913   0.09758  -0.0194   1.0000   0.0066
 -10.000  -0.3886   0.09475   0.09321  -0.0208   1.0000   0.0067
  -9.750  -0.3879   0.09053   0.08900  -0.0221   1.0000   0.0069
  -9.500  -0.3868   0.08641   0.08489  -0.0233   1.0000   0.0069
  -9.250  -0.3864   0.08219   0.08068  -0.0246   1.0000   0.0070
  -9.000  -0.3861   0.07809   0.07660  -0.0259   1.0000   0.0071
  -8.750  -0.3867   0.07394   0.07245  -0.0272   1.0000   0.0072
  -8.500  -0.3886   0.06962   0.06816  -0.0286   1.0000   0.0072
  -8.250  -0.3924   0.06508   0.06364  -0.0302   1.0000   0.0073
  -8.000  -0.3973   0.06068   0.05925  -0.0319   1.0000   0.0073
  -7.750  -0.4063   0.05611   0.05471  -0.0338   1.0000   0.0073
  -7.500  -0.4259   0.05073   0.04938  -0.0378   1.0000   0.0072
  -7.250  -0.4393   0.04484   0.04345  -0.0419   1.0000   0.0071
  -7.000  -0.4275   0.03766   0.03613  -0.0490   0.9959   0.0072
  -6.750  -0.4098   0.03149   0.02980  -0.0544   0.9908   0.0074
  -6.500  -0.3884   0.02597   0.02408  -0.0587   0.9861   0.0076
  -6.250  -0.3640   0.02094   0.01882  -0.0622   0.9820   0.0080
  -6.000  -0.3421   0.01675   0.01437  -0.0640   0.9733   0.0084
  -5.250  -0.2841   0.01711   0.01324  -0.0669   0.9655   0.0080
  -5.000  -0.2565   0.01347   0.00908  -0.0660   0.9567   0.0060
  -4.500  -0.2066   0.01005   0.00515  -0.0648   0.9375   0.0076
  -4.250  -0.1806   0.00952   0.00454  -0.0644   0.9285   0.0083
  -4.000  -0.1546   0.00898   0.00391  -0.0639   0.9193   0.0088
  -3.750  -0.1282   0.00862   0.00348  -0.0636   0.9111   0.0097
  -3.500  -0.1018   0.00820   0.00295  -0.0632   0.9027   0.0104
  -3.250  -0.0750   0.00778   0.00241  -0.0628   0.8945   0.0109
  -3.000  -0.0482   0.00735   0.00181  -0.0624   0.8868   0.0144
  -2.750  -0.0212   0.00700   0.00154  -0.0622   0.8784   0.0406
  -2.250   0.0325   0.00644   0.00124  -0.0619   0.8620   0.1382
  -2.000   0.0586   0.00590   0.00109  -0.0619   0.8525   0.2678
  -1.750   0.0830   0.00505   0.00096  -0.0617   0.8424   0.5101
  -1.500   0.1096   0.00488   0.00091  -0.0614   0.8323   0.5779
  -1.250   0.1370   0.00480   0.00088  -0.0613   0.8223   0.6145
  -1.000   0.1645   0.00475   0.00085  -0.0611   0.8126   0.6412
  -0.750   0.1918   0.00471   0.00082  -0.0609   0.8023   0.6657
  -0.500   0.2190   0.00468   0.00081  -0.0607   0.7916   0.6940
  -0.250   0.2458   0.00463   0.00083  -0.0604   0.7796   0.7285
   0.000   0.2731   0.00462   0.00083  -0.0601   0.7679   0.7509
   0.250   0.3003   0.00461   0.00084  -0.0599   0.7570   0.7697
   0.500   0.3275   0.00461   0.00085  -0.0597   0.7452   0.7878
   0.750   0.3547   0.00462   0.00086  -0.0595   0.7320   0.8015
   1.000   0.3819   0.00464   0.00087  -0.0593   0.7186   0.8150
   1.250   0.4088   0.00466   0.00089  -0.0590   0.7033   0.8302
   1.500   0.4353   0.00468   0.00093  -0.0587   0.6866   0.8477
   1.750   0.4612   0.00469   0.00096  -0.0582   0.6688   0.8710
   2.000   0.4854   0.00465   0.00100  -0.0572   0.6484   0.9122
   2.250   0.5229   0.00467   0.00103  -0.0593   0.6213   1.0000
   2.500   0.5491   0.00487   0.00110  -0.0590   0.5868   1.0000
   2.750   0.5737   0.00525   0.00122  -0.0585   0.5182   1.0000
   3.000   0.5975   0.00576   0.00138  -0.0579   0.4370   1.0000
   3.250   0.6227   0.00613   0.00154  -0.0576   0.3841   1.0000
   3.500   0.6478   0.00653   0.00173  -0.0572   0.3300   1.0000
   3.750   0.6724   0.00700   0.00194  -0.0568   0.2736   1.0000
   4.000   0.6981   0.00734   0.00216  -0.0566   0.2402   1.0000
   4.250   0.7240   0.00764   0.00235  -0.0563   0.2122   1.0000
   4.500   0.7488   0.00807   0.00258  -0.0560   0.1667   1.0000
   4.750   0.7729   0.00861   0.00287  -0.0555   0.1162   1.0000
   5.000   0.7967   0.00920   0.00323  -0.0550   0.0711   1.0000
   5.250   0.8213   0.00967   0.00358  -0.0546   0.0459   1.0000
   5.500   0.8468   0.01000   0.00387  -0.0544   0.0346   1.0000
   5.750   0.8722   0.01035   0.00416  -0.0540   0.0242   1.0000
   6.000   0.8965   0.01088   0.00460  -0.0535   0.0098   1.0000
   6.250   0.9212   0.01133   0.00504  -0.0530   0.0057   1.0000
   6.500   0.9462   0.01174   0.00551  -0.0526   0.0050   1.0000
   6.750   0.9709   0.01219   0.00601  -0.0521   0.0046   1.0000
   7.000   0.9950   0.01272   0.00665  -0.0515   0.0042   1.0000
   7.250   1.0180   0.01342   0.00745  -0.0507   0.0037   1.0000
   7.500   1.0368   0.01480   0.00905  -0.0491   0.0032   1.0000
   7.750   1.0593   0.01553   0.00988  -0.0483   0.0030   1.0000
   8.000   1.0796   0.01657   0.01106  -0.0471   0.0030   1.0000
   8.250   1.0983   0.01789   0.01255  -0.0457   0.0029   1.0000
   8.500   1.1160   0.01942   0.01426  -0.0442   0.0029   1.0000
   8.750   1.1316   0.02138   0.01645  -0.0423   0.0029   1.0000
   9.000   1.1452   0.02377   0.01911  -0.0404   0.0030   1.0000
   9.250   1.1510   0.02775   0.02346  -0.0375   0.0033   1.0000
   9.500   1.1688   0.02876   0.02461  -0.0363   0.0035   1.0000
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