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HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/8 AIRFOIL (hq208-il)
Reynolds number: 1,000,000
Max Cl/Cd: 84.53 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq208-il-1000000-n5.txt
Download as CSV file: xf-hq208-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4884   0.11982   0.11811  -0.0087   1.0000   0.0027
 -10.750  -0.4848   0.11584   0.11414  -0.0102   1.0000   0.0028
  -7.250  -0.4642   0.05182   0.05017  -0.0513   0.9877   0.0030
  -7.000  -0.4430   0.04312   0.04120  -0.0593   0.9779   0.0029
  -6.750  -0.4214   0.03442   0.03212  -0.0644   0.9653   0.0027
  -6.250  -0.3895   0.01690   0.01304  -0.0651   0.9308   0.0025
  -6.000  -0.3670   0.01430   0.00998  -0.0644   0.9185   0.0025
  -5.750  -0.3429   0.01265   0.00800  -0.0638   0.9079   0.0025
  -5.500  -0.3181   0.01142   0.00652  -0.0632   0.8985   0.0026
  -5.250  -0.2926   0.01055   0.00546  -0.0628   0.8901   0.0028
  -5.000  -0.2665   0.00994   0.00471  -0.0624   0.8819   0.0030
  -4.750  -0.2398   0.00957   0.00425  -0.0622   0.8747   0.0032
  -4.500  -0.2138   0.00889   0.00342  -0.0619   0.8672   0.0040
  -4.250  -0.1867   0.00862   0.00310  -0.0618   0.8606   0.0046
  -4.000  -0.1596   0.00834   0.00276  -0.0617   0.8537   0.0053
  -3.750  -0.1322   0.00814   0.00249  -0.0616   0.8472   0.0061
  -3.500  -0.1049   0.00791   0.00220  -0.0615   0.8403   0.0074
  -3.250  -0.0774   0.00765   0.00188  -0.0614   0.8335   0.0092
  -3.000  -0.0499   0.00749   0.00164  -0.0613   0.8260   0.0105
  -2.750  -0.0222   0.00734   0.00145  -0.0612   0.8180   0.0127
  -2.500   0.0051   0.00715   0.00129  -0.0611   0.8092   0.0284
  -2.250   0.0327   0.00702   0.00116  -0.0611   0.7991   0.0423
  -2.000   0.0600   0.00691   0.00104  -0.0610   0.7861   0.0579
  -1.750   0.0871   0.00679   0.00094  -0.0608   0.7699   0.0824
  -1.500   0.1138   0.00648   0.00081  -0.0608   0.7544   0.1634
  -1.250   0.1400   0.00594   0.00070  -0.0608   0.7406   0.3198
  -1.000   0.1666   0.00562   0.00063  -0.0608   0.7263   0.4251
  -0.750   0.1936   0.00545   0.00060  -0.0607   0.7115   0.4933
  -0.500   0.2204   0.00530   0.00059  -0.0606   0.6943   0.5655
  -0.250   0.2469   0.00521   0.00062  -0.0603   0.6757   0.6328
   0.000   0.2740   0.00520   0.00064  -0.0602   0.6594   0.6653
   0.250   0.3014   0.00522   0.00066  -0.0600   0.6445   0.6880
   0.500   0.3285   0.00525   0.00069  -0.0599   0.6261   0.7079
   1.000   0.3831   0.00540   0.00075  -0.0596   0.5871   0.7303
   1.250   0.4101   0.00552   0.00080  -0.0595   0.5608   0.7407
   1.500   0.4369   0.00566   0.00087  -0.0593   0.5306   0.7513
   1.750   0.4633   0.00584   0.00095  -0.0591   0.4946   0.7622
   2.000   0.4895   0.00605   0.00104  -0.0588   0.4559   0.7738
   2.250   0.5150   0.00635   0.00117  -0.0585   0.4042   0.7860
   2.500   0.5390   0.00685   0.00136  -0.0580   0.3205   0.7991
   2.750   0.5632   0.00730   0.00158  -0.0575   0.2531   0.8138
   3.000   0.5883   0.00759   0.00174  -0.0571   0.2117   0.8309
   3.250   0.6139   0.00775   0.00188  -0.0567   0.1884   0.8519
   3.500   0.6384   0.00783   0.00202  -0.0560   0.1716   0.8863
   3.750   0.6703   0.00793   0.00217  -0.0570   0.1463   1.0000
   4.000   0.6961   0.00827   0.00240  -0.0568   0.1165   1.0000
   4.250   0.7201   0.00886   0.00273  -0.0563   0.0647   1.0000
   4.500   0.7452   0.00928   0.00302  -0.0560   0.0386   1.0000
   4.750   0.7711   0.00958   0.00326  -0.0558   0.0269   1.0000
   5.000   0.7965   0.00996   0.00355  -0.0555   0.0150   1.0000
   5.250   0.8218   0.01035   0.00390  -0.0551   0.0053   1.0000
   5.500   0.8477   0.01065   0.00422  -0.0548   0.0032   1.0000
   5.750   0.8735   0.01096   0.00457  -0.0545   0.0027   1.0000
   6.000   0.8990   0.01129   0.00495  -0.0542   0.0024   1.0000
   6.250   0.9243   0.01166   0.00537  -0.0538   0.0022   1.0000
   6.500   0.9490   0.01212   0.00590  -0.0534   0.0018   1.0000
   6.750   0.9723   0.01281   0.00670  -0.0526   0.0015   1.0000
   7.000   0.9960   0.01340   0.00736  -0.0520   0.0013   1.0000
   7.250   1.0200   0.01393   0.00799  -0.0515   0.0013   1.0000
   7.500   1.0429   0.01463   0.00878  -0.0507   0.0012   1.0000
   7.750   1.0654   0.01536   0.00960  -0.0500   0.0011   1.0000
   8.000   1.0869   0.01622   0.01058  -0.0490   0.0011   1.0000
   8.250   1.1075   0.01718   0.01167  -0.0480   0.0011   1.0000
   8.500   1.1270   0.01830   0.01292  -0.0468   0.0011   1.0000
   8.750   1.1460   0.01946   0.01424  -0.0456   0.0010   1.0000
   9.000   1.1637   0.02081   0.01576  -0.0442   0.0010   1.0000
   9.250   1.1801   0.02231   0.01745  -0.0427   0.0010   1.0000
   9.500   1.1954   0.02391   0.01924  -0.0411   0.0010   1.0000
   9.750   1.2081   0.02579   0.02136  -0.0392   0.0010   1.0000
  10.000   1.2189   0.02777   0.02360  -0.0372   0.0010   1.0000
  10.250   1.2262   0.02998   0.02607  -0.0349   0.0010   1.0000
  10.500   1.2281   0.03257   0.02893  -0.0321   0.0010   1.0000
  10.750   1.2235   0.03496   0.03156  -0.0284   0.0010   1.0000
  11.000   1.2155   0.03727   0.03408  -0.0247   0.0010   1.0000
  11.250   1.2027   0.04021   0.03724  -0.0215   0.0010   1.0000
  11.500   1.1907   0.04332   0.04054  -0.0195   0.0010   1.0000
  11.750   1.1739   0.04738   0.04481  -0.0185   0.0010   1.0000
  12.000   1.1576   0.05192   0.04953  -0.0188   0.0010   1.0000
  12.250   1.1399   0.05735   0.05514  -0.0206   0.0010   1.0000
  12.500   1.1222   0.06371   0.06165  -0.0240   0.0011   1.0000
  12.750   1.1035   0.07154   0.06964  -0.0291   0.0011   1.0000
  13.000   1.0822   0.08170   0.07995  -0.0363   0.0011   1.0000
  13.250   1.0620   0.09311   0.09149  -0.0438   0.0011   1.0000
  13.500   1.0420   0.10438   0.10284  -0.0503   0.0011   1.0000
  13.750   1.0165   0.11709   0.11563  -0.0569   0.0011   1.0000
  14.000   0.9882   0.13092   0.12947  -0.0635   0.0011   1.0000
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