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HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il)
Reynolds number: 200,000
Max Cl/Cd: 65.77 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2012-il-200000-n5.txt
Download as CSV file: xf-hq2012-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6915   0.05513   0.05099  -0.0626   1.0000   0.0126
 -11.500  -0.7123   0.04956   0.04520  -0.0660   1.0000   0.0126
 -11.250  -0.7301   0.04529   0.04074  -0.0675   1.0000   0.0126
 -11.000  -0.7460   0.04197   0.03723  -0.0672   1.0000   0.0127
 -10.750  -0.7603   0.03954   0.03465  -0.0649   1.0000   0.0127
 -10.500  -0.7657   0.03754   0.03251  -0.0626   1.0000   0.0130
 -10.250  -0.7673   0.03557   0.03038  -0.0604   1.0000   0.0131
 -10.000  -0.7655   0.03390   0.02853  -0.0580   1.0000   0.0134
  -9.750  -0.7631   0.03223   0.02668  -0.0554   1.0000   0.0136
  -9.500  -0.7604   0.03081   0.02510  -0.0526   1.0000   0.0139
  -9.250  -0.7362   0.02877   0.02279  -0.0539   0.9941   0.0145
  -9.000  -0.7097   0.02680   0.02053  -0.0553   0.9873   0.0153
  -8.750  -0.6801   0.02522   0.01863  -0.0568   0.9820   0.0165
  -8.500  -0.6525   0.02378   0.01706  -0.0580   0.9754   0.0176
  -8.250  -0.6208   0.02270   0.01585  -0.0598   0.9709   0.0187
  -8.000  -0.5934   0.02158   0.01459  -0.0604   0.9633   0.0199
  -7.750  -0.5628   0.02043   0.01326  -0.0616   0.9578   0.0216
  -7.500  -0.5357   0.01934   0.01208  -0.0621   0.9502   0.0233
  -7.250  -0.5050   0.01867   0.01134  -0.0632   0.9441   0.0263
  -7.000  -0.4762   0.01799   0.01053  -0.0637   0.9370   0.0296
  -6.750  -0.4477   0.01724   0.00975  -0.0644   0.9301   0.0339
  -6.500  -0.4191   0.01670   0.00908  -0.0648   0.9233   0.0382
  -6.250  -0.3914   0.01611   0.00849  -0.0651   0.9162   0.0439
  -6.000  -0.3630   0.01573   0.00801  -0.0654   0.9097   0.0498
  -5.750  -0.3369   0.01517   0.00744  -0.0654   0.9023   0.0562
  -5.500  -0.3097   0.01478   0.00695  -0.0654   0.8958   0.0628
  -5.250  -0.2843   0.01433   0.00650  -0.0651   0.8883   0.0712
  -5.000  -0.2579   0.01391   0.00604  -0.0649   0.8820   0.0799
  -4.750  -0.2326   0.01354   0.00566  -0.0645   0.8745   0.0918
  -4.500  -0.2064   0.01314   0.00528  -0.0643   0.8687   0.1116
  -4.250  -0.1816   0.01276   0.00498  -0.0640   0.8610   0.1391
  -4.000  -0.1558   0.01237   0.00469  -0.0637   0.8551   0.1761
  -3.750  -0.1311   0.01197   0.00444  -0.0634   0.8479   0.2234
  -3.500  -0.1065   0.01148   0.00415  -0.0630   0.8416   0.2885
  -3.250  -0.0841   0.01083   0.00399  -0.0623   0.8349   0.4081
  -3.000  -0.0597   0.01053   0.00395  -0.0616   0.8282   0.4906
  -2.750  -0.0337   0.01042   0.00392  -0.0611   0.8223   0.5391
  -2.500  -0.0076   0.01037   0.00391  -0.0606   0.8152   0.5754
  -2.250   0.0194   0.01035   0.00388  -0.0601   0.8097   0.6041
  -2.000   0.0457   0.01034   0.00388  -0.0596   0.8022   0.6262
  -1.750   0.0729   0.01034   0.00384  -0.0593   0.7962   0.6445
  -1.500   0.0996   0.01035   0.00383  -0.0589   0.7888   0.6605
  -1.250   0.1267   0.01035   0.00379  -0.0585   0.7822   0.6753
  -1.000   0.1535   0.01035   0.00379  -0.0581   0.7747   0.6886
  -0.750   0.1804   0.01035   0.00378  -0.0576   0.7679   0.7029
  -0.500   0.2069   0.01036   0.00378  -0.0571   0.7594   0.7155
  -0.250   0.2342   0.01034   0.00370  -0.0568   0.7509   0.7242
   0.000   0.2610   0.01032   0.00366  -0.0564   0.7402   0.7312
   0.250   0.2881   0.01031   0.00362  -0.0562   0.7303   0.7386
   0.500   0.3153   0.01030   0.00358  -0.0558   0.7211   0.7457
   0.750   0.3423   0.01030   0.00356  -0.0555   0.7106   0.7533
   1.000   0.3690   0.01030   0.00356  -0.0551   0.6997   0.7608
   1.250   0.3958   0.01031   0.00354  -0.0548   0.6884   0.7686
   1.500   0.4225   0.01033   0.00354  -0.0544   0.6776   0.7767
   1.750   0.4491   0.01034   0.00358  -0.0540   0.6669   0.7847
   2.000   0.4757   0.01037   0.00362  -0.0537   0.6561   0.7935
   2.250   0.5019   0.01040   0.00366  -0.0532   0.6443   0.8020
   2.500   0.5282   0.01044   0.00371  -0.0528   0.6318   0.8116
   2.750   0.5542   0.01047   0.00377  -0.0523   0.6187   0.8214
   3.000   0.5800   0.01052   0.00384  -0.0518   0.6035   0.8319
   3.250   0.6055   0.01057   0.00391  -0.0512   0.5862   0.8437
   3.500   0.6307   0.01063   0.00400  -0.0505   0.5671   0.8569
   3.750   0.6557   0.01072   0.00408  -0.0498   0.5452   0.8721
   4.000   0.6811   0.01084   0.00418  -0.0492   0.5186   0.8918
   4.250   0.7099   0.01102   0.00432  -0.0494   0.4872   0.9180
   4.500   0.7452   0.01133   0.00452  -0.0512   0.4464   0.9680
   4.750   0.7699   0.01175   0.00476  -0.0509   0.4076   1.0000
   5.000   0.7908   0.01223   0.00505  -0.0499   0.3710   1.0000
   5.250   0.8120   0.01271   0.00538  -0.0490   0.3362   1.0000
   5.500   0.8329   0.01323   0.00573  -0.0480   0.3062   1.0000
   5.750   0.8538   0.01375   0.00612  -0.0470   0.2827   1.0000
   6.000   0.8754   0.01422   0.00650  -0.0462   0.2630   1.0000
   6.250   0.8972   0.01468   0.00692  -0.0454   0.2458   1.0000
   6.500   0.9194   0.01510   0.00732  -0.0446   0.2313   1.0000
   6.750   0.9417   0.01551   0.00773  -0.0439   0.2180   1.0000
   7.000   0.9637   0.01593   0.00814  -0.0431   0.2042   1.0000
   7.250   0.9850   0.01638   0.00857  -0.0422   0.1875   1.0000
   7.500   1.0053   0.01689   0.00904  -0.0412   0.1683   1.0000
   7.750   1.0251   0.01743   0.00954  -0.0402   0.1472   1.0000
   8.000   1.0431   0.01809   0.01011  -0.0389   0.1268   1.0000
   8.250   1.0605   0.01879   0.01074  -0.0375   0.1084   1.0000
   8.500   1.0768   0.01955   0.01144  -0.0361   0.0932   1.0000
   8.750   1.0925   0.02032   0.01220  -0.0345   0.0816   1.0000
   9.000   1.1063   0.02110   0.01297  -0.0326   0.0729   1.0000
   9.250   1.1201   0.02184   0.01374  -0.0307   0.0663   1.0000
   9.500   1.1323   0.02268   0.01458  -0.0287   0.0607   1.0000
   9.750   1.1459   0.02345   0.01540  -0.0270   0.0550   1.0000
  10.000   1.1562   0.02444   0.01639  -0.0250   0.0508   1.0000
  10.250   1.1707   0.02518   0.01722  -0.0235   0.0468   1.0000
  10.500   1.1827   0.02609   0.01823  -0.0219   0.0440   1.0000
  10.750   1.1931   0.02713   0.01933  -0.0203   0.0417   1.0000
  11.000   1.2013   0.02837   0.02061  -0.0185   0.0398   1.0000
  11.250   1.2127   0.02941   0.02179  -0.0171   0.0384   1.0000
  11.500   1.2237   0.03051   0.02302  -0.0158   0.0364   1.0000
  11.750   1.2341   0.03167   0.02428  -0.0146   0.0341   1.0000
  12.000   1.2416   0.03310   0.02572  -0.0134   0.0312   1.0000
  12.250   1.2523   0.03432   0.02707  -0.0125   0.0287   1.0000
  12.500   1.2616   0.03569   0.02859  -0.0115   0.0264   1.0000
  12.750   1.2689   0.03726   0.03023  -0.0106   0.0240   1.0000
  13.000   1.2755   0.03896   0.03202  -0.0098   0.0217   1.0000
  13.250   1.2818   0.04073   0.03392  -0.0091   0.0193   1.0000
  13.500   1.2854   0.04282   0.03608  -0.0085   0.0173   1.0000
  13.750   1.2880   0.04510   0.03848  -0.0080   0.0148   1.0000
  14.000   1.2883   0.04770   0.04119  -0.0077   0.0135   1.0000
  14.250   1.2861   0.05067   0.04425  -0.0077   0.0124   1.0000
  14.500   1.2830   0.05389   0.04764  -0.0078   0.0110   1.0000
  14.750   1.2792   0.05733   0.05123  -0.0083   0.0105   1.0000
  15.000   1.2730   0.06126   0.05529  -0.0091   0.0098   1.0000
  15.250   1.2637   0.06585   0.06001  -0.0105   0.0092   1.0000
  15.500   1.2550   0.07061   0.06492  -0.0122   0.0090   1.0000
  15.750   1.2451   0.07580   0.07028  -0.0142   0.0089   1.0000
  16.000   1.2336   0.08153   0.07619  -0.0168   0.0087   1.0000
  16.250   1.2209   0.08774   0.08257  -0.0198   0.0086   1.0000
  16.500   1.2061   0.09460   0.08962  -0.0233   0.0085   1.0000
  16.750   1.1903   0.10191   0.09710  -0.0271   0.0084   1.0000
  17.000   1.1745   0.10947   0.10482  -0.0312   0.0085   1.0000
  17.250   1.1572   0.11754   0.11306  -0.0357   0.0084   1.0000
  17.500   1.1392   0.12595   0.12162  -0.0404   0.0084   1.0000
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