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HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il)
Reynolds number: 100,000
Max Cl/Cd: 51.22 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2012-il-100000-n5.txt
Download as CSV file: xf-hq2012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/12 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4860   0.09462   0.08950  -0.0387   1.0000   0.0274
 -10.750  -0.4969   0.08766   0.08260  -0.0423   1.0000   0.0272
 -10.500  -0.5170   0.07768   0.07268  -0.0481   1.0000   0.0267
 -10.250  -0.5498   0.06652   0.06149  -0.0566   1.0000   0.0259
 -10.000  -0.5816   0.05944   0.05433  -0.0613   1.0000   0.0256
  -9.750  -0.6096   0.05499   0.04977  -0.0620   1.0000   0.0252
  -9.500  -0.6329   0.05150   0.04612  -0.0602   1.0000   0.0252
  -9.250  -0.6495   0.04809   0.04249  -0.0580   1.0000   0.0253
  -9.000  -0.6608   0.04498   0.03913  -0.0554   1.0000   0.0255
  -8.750  -0.6686   0.04214   0.03601  -0.0524   1.0000   0.0258
  -8.500  -0.6733   0.03956   0.03312  -0.0492   1.0000   0.0263
  -8.250  -0.6745   0.03715   0.03038  -0.0461   1.0000   0.0268
  -8.000  -0.6660   0.03447   0.02724  -0.0445   0.9982   0.0278
  -7.750  -0.6388   0.03159   0.02379  -0.0461   0.9920   0.0298
  -7.500  -0.6097   0.03009   0.02224  -0.0478   0.9860   0.0322
  -7.250  -0.5798   0.02844   0.02031  -0.0492   0.9803   0.0353
  -7.000  -0.5496   0.02661   0.01810  -0.0501   0.9746   0.0382
  -6.750  -0.5180   0.02531   0.01681  -0.0519   0.9699   0.0428
  -6.500  -0.4891   0.02424   0.01549  -0.0525   0.9631   0.0483
  -6.250  -0.4569   0.02313   0.01436  -0.0541   0.9582   0.0550
  -6.000  -0.4264   0.02226   0.01330  -0.0549   0.9524   0.0620
  -5.750  -0.3964   0.02134   0.01241  -0.0560   0.9465   0.0702
  -5.500  -0.3626   0.02048   0.01149  -0.0576   0.9423   0.0800
  -5.250  -0.3361   0.01983   0.01075  -0.0576   0.9348   0.0890
  -5.000  -0.3047   0.01911   0.01003  -0.0587   0.9295   0.1027
  -4.750  -0.2770   0.01843   0.00943  -0.0591   0.9230   0.1199
  -4.500  -0.2481   0.01780   0.00885  -0.0597   0.9168   0.1466
  -4.250  -0.2176   0.01708   0.00834  -0.0607   0.9119   0.1960
  -4.000  -0.1936   0.01639   0.00793  -0.0605   0.9042   0.2638
  -3.750  -0.1667   0.01548   0.00763  -0.0609   0.8991   0.3875
  -3.500  -0.1445   0.01517   0.00768  -0.0597   0.8913   0.4967
  -3.250  -0.1160   0.01510   0.00772  -0.0594   0.8858   0.5623
  -3.000  -0.0900   0.01515   0.00776  -0.0586   0.8790   0.6048
  -2.750  -0.0628   0.01521   0.00779  -0.0580   0.8726   0.6372
  -2.500  -0.0344   0.01526   0.00777  -0.0577   0.8672   0.6639
  -2.250  -0.0096   0.01534   0.00781  -0.0567   0.8596   0.6841
  -2.000   0.0200   0.01534   0.00774  -0.0566   0.8547   0.7022
  -1.750   0.0435   0.01542   0.00776  -0.0555   0.8465   0.7183
  -1.500   0.0712   0.01544   0.00773  -0.0549   0.8409   0.7372
  -1.250   0.0944   0.01550   0.00779  -0.0536   0.8332   0.7539
  -1.000   0.1216   0.01548   0.00771  -0.0531   0.8270   0.7677
  -0.750   0.1473   0.01546   0.00766  -0.0525   0.8195   0.7768
  -0.500   0.1752   0.01540   0.00756  -0.0523   0.8127   0.7853
  -0.250   0.2016   0.01538   0.00749  -0.0520   0.8053   0.7950
   0.000   0.2287   0.01532   0.00741  -0.0516   0.7982   0.8033
   0.250   0.2549   0.01530   0.00737  -0.0512   0.7907   0.8129
   0.500   0.2822   0.01524   0.00728  -0.0508   0.7832   0.8227
   0.750   0.3078   0.01518   0.00724  -0.0502   0.7738   0.8324
   1.000   0.3361   0.01503   0.00706  -0.0498   0.7650   0.8428
   1.500   0.3877   0.01480   0.00685  -0.0483   0.7414   0.8655
   1.750   0.4146   0.01468   0.00674  -0.0477   0.7291   0.8778
   2.000   0.4431   0.01457   0.00666  -0.0475   0.7176   0.8915
   2.250   0.4747   0.01446   0.00658  -0.0479   0.7075   0.9060
   2.500   0.5077   0.01444   0.00662  -0.0489   0.6953   0.9228
   2.750   0.5439   0.01442   0.00666  -0.0505   0.6826   0.9426
   3.000   0.5823   0.01439   0.00667  -0.0526   0.6688   0.9671
   3.250   0.6186   0.01440   0.00669  -0.0545   0.6540   1.0000
   3.500   0.6416   0.01448   0.00677  -0.0537   0.6390   1.0000
   3.750   0.6658   0.01457   0.00684  -0.0530   0.6227   1.0000
   4.000   0.6904   0.01467   0.00690  -0.0524   0.6049   1.0000
   4.250   0.7140   0.01481   0.00705  -0.0516   0.5835   1.0000
   4.500   0.7381   0.01496   0.00717  -0.0508   0.5605   1.0000
   4.750   0.7615   0.01516   0.00731  -0.0499   0.5333   1.0000
   5.000   0.7843   0.01541   0.00747  -0.0489   0.5025   1.0000
   5.250   0.8062   0.01574   0.00771  -0.0478   0.4682   1.0000
   5.500   0.8271   0.01618   0.00798  -0.0466   0.4324   1.0000
   5.750   0.8472   0.01670   0.00833  -0.0453   0.3979   1.0000
   6.000   0.8670   0.01726   0.00876  -0.0441   0.3663   1.0000
   6.250   0.8866   0.01786   0.00922  -0.0428   0.3376   1.0000
   6.500   0.9056   0.01850   0.00975  -0.0416   0.3123   1.0000
   6.750   0.9250   0.01912   0.01030  -0.0404   0.2898   1.0000
   7.000   0.9438   0.01979   0.01088  -0.0392   0.2702   1.0000
   7.250   0.9629   0.02044   0.01149  -0.0381   0.2516   1.0000
   7.500   0.9819   0.02106   0.01216  -0.0370   0.2330   1.0000
   7.750   1.0004   0.02170   0.01281  -0.0358   0.2148   1.0000
   8.000   1.0178   0.02238   0.01348  -0.0344   0.1965   1.0000
   8.250   1.0356   0.02304   0.01419  -0.0332   0.1769   1.0000
   8.500   1.0509   0.02383   0.01495  -0.0316   0.1556   1.0000
   8.750   1.0649   0.02472   0.01579  -0.0300   0.1348   1.0000
   9.000   1.0763   0.02573   0.01675  -0.0280   0.1179   1.0000
   9.250   1.0867   0.02679   0.01779  -0.0259   0.1059   1.0000
   9.500   1.0961   0.02796   0.01895  -0.0237   0.0971   1.0000
   9.750   1.1054   0.02918   0.02020  -0.0217   0.0895   1.0000
  10.000   1.1147   0.03045   0.02151  -0.0198   0.0835   1.0000
  10.250   1.1240   0.03173   0.02287  -0.0181   0.0780   1.0000
  10.500   1.1305   0.03326   0.02439  -0.0163   0.0740   1.0000
  10.750   1.1412   0.03460   0.02590  -0.0148   0.0704   1.0000
  11.000   1.1503   0.03607   0.02752  -0.0134   0.0670   1.0000
  11.250   1.1572   0.03768   0.02919  -0.0120   0.0640   1.0000
  11.500   1.1647   0.03945   0.03101  -0.0107   0.0614   1.0000
  11.750   1.1742   0.04107   0.03284  -0.0095   0.0587   1.0000
  12.000   1.1815   0.04283   0.03476  -0.0085   0.0559   1.0000
  12.250   1.1862   0.04470   0.03672  -0.0075   0.0532   1.0000
  12.500   1.1889   0.04690   0.03891  -0.0067   0.0504   1.0000
  12.750   1.1927   0.04904   0.04135  -0.0060   0.0479   1.0000
  13.000   1.1935   0.05137   0.04388  -0.0056   0.0448   1.0000
  13.250   1.1934   0.05390   0.04654  -0.0054   0.0426   1.0000
  13.500   1.1912   0.05675   0.04949  -0.0055   0.0407   1.0000
  13.750   1.1886   0.05992   0.05286  -0.0057   0.0386   1.0000
  14.000   1.1853   0.06332   0.05653  -0.0061   0.0366   1.0000
  14.250   1.1801   0.06703   0.06042  -0.0070   0.0347   1.0000
  14.500   1.1731   0.07109   0.06463  -0.0085   0.0329   1.0000
  14.750   1.1654   0.07548   0.06913  -0.0101   0.0317   1.0000
  15.000   1.1567   0.08024   0.07395  -0.0120   0.0306   1.0000
  15.250   1.1452   0.08601   0.08004  -0.0145   0.0294   1.0000
  15.500   1.1324   0.09222   0.08649  -0.0175   0.0285   1.0000
  15.750   1.1180   0.09903   0.09353  -0.0210   0.0278   1.0000
  16.000   1.1016   0.10659   0.10130  -0.0252   0.0271   1.0000
  16.250   1.0834   0.11486   0.10976  -0.0299   0.0269   1.0000
  16.500   1.0610   0.12457   0.11966  -0.0356   0.0268   1.0000
  16.750   1.0318   0.13657   0.13185  -0.0428   0.0273   1.0000
  17.000   0.9924   0.15223   0.14760  -0.0520   0.0285   1.0000
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