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HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il)
Reynolds number: 100,000
Max Cl/Cd: 49.93 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1512-il-100000.txt
Download as CSV file: xf-hq1512-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/12 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4739   0.09689   0.09194  -0.0275   1.0000   0.1499
  -9.500  -0.4788   0.06534   0.06083  -0.0481   1.0000   0.0867
  -9.250  -0.5318   0.05497   0.05036  -0.0536   1.0000   0.0751
  -9.000  -0.6118   0.06230   0.05738  -0.0515   1.0000   0.0766
  -8.750  -0.6536   0.05501   0.04957  -0.0503   1.0000   0.0678
  -8.500  -0.6596   0.05091   0.04529  -0.0483   1.0000   0.0660
  -8.250  -0.6661   0.04688   0.04097  -0.0458   1.0000   0.0642
  -8.000  -0.6709   0.04316   0.03688  -0.0428   1.0000   0.0631
  -7.750  -0.6707   0.04040   0.03381  -0.0398   1.0000   0.0636
  -7.500  -0.6680   0.03806   0.03115  -0.0368   1.0000   0.0651
  -7.250  -0.6631   0.03563   0.02834  -0.0339   1.0000   0.0663
  -7.000  -0.6548   0.03318   0.02549  -0.0313   1.0000   0.0670
  -6.750  -0.6434   0.03104   0.02294  -0.0289   1.0000   0.0682
  -6.500  -0.6299   0.02942   0.02087  -0.0267   1.0000   0.0703
  -6.250  -0.6145   0.02743   0.01895  -0.0253   1.0000   0.0748
  -6.000  -0.5977   0.02617   0.01749  -0.0236   1.0000   0.0799
  -5.750  -0.5793   0.02464   0.01574  -0.0220   1.0000   0.0846
  -5.500  -0.5619   0.02360   0.01475  -0.0207   1.0000   0.0932
  -5.250  -0.5439   0.02244   0.01364  -0.0193   1.0000   0.1035
  -5.000  -0.5262   0.02146   0.01270  -0.0180   1.0000   0.1178
  -4.750  -0.5085   0.02060   0.01187  -0.0166   1.0000   0.1385
  -4.500  -0.4914   0.01969   0.01114  -0.0154   1.0000   0.1674
  -4.250  -0.4746   0.01875   0.01053  -0.0142   1.0000   0.2126
  -4.000  -0.4432   0.01730   0.00992  -0.0161   0.9946   0.3247
  -3.750  -0.4161   0.01655   0.01023  -0.0163   0.9881   0.5233
  -3.500  -0.3826   0.01707   0.01090  -0.0168   0.9815   0.6181
  -3.250  -0.3534   0.01756   0.01137  -0.0165   0.9737   0.6679
  -3.000  -0.3212   0.01813   0.01190  -0.0166   0.9670   0.7059
  -2.750  -0.2939   0.01853   0.01222  -0.0159   0.9592   0.7354
  -2.500  -0.2629   0.01890   0.01252  -0.0159   0.9524   0.7622
  -2.250  -0.2373   0.01915   0.01274  -0.0148   0.9445   0.7838
  -2.000  -0.2077   0.01938   0.01289  -0.0147   0.9376   0.8073
  -1.750  -0.1832   0.01951   0.01298  -0.0134   0.9296   0.8271
  -1.500  -0.1538   0.01964   0.01305  -0.0133   0.9229   0.8467
  -1.250  -0.1282   0.01968   0.01303  -0.0127   0.9147   0.8656
  -1.000  -0.0947   0.01979   0.01309  -0.0132   0.9085   0.8836
  -0.750  -0.0640   0.01993   0.01319  -0.0132   0.9007   0.9041
  -0.500  -0.0092   0.02012   0.01331  -0.0178   0.8967   0.9214
  -0.250   0.0344   0.02031   0.01345  -0.0211   0.8890   0.9343
   0.000   0.0930   0.02036   0.01343  -0.0272   0.8841   0.9426
   0.250   0.1633   0.02032   0.01333  -0.0353   0.8813   0.9477
   0.500   0.2094   0.02038   0.01338  -0.0394   0.8721   0.9570
   0.750   0.2839   0.01986   0.01283  -0.0475   0.8667   0.9598
   1.000   0.3334   0.01950   0.01247  -0.0513   0.8547   0.9679
   1.250   0.3893   0.01899   0.01197  -0.0561   0.8432   0.9739
   1.500   0.4380   0.01855   0.01155  -0.0597   0.8332   0.9819
   1.750   0.4883   0.01811   0.01115  -0.0639   0.8231   0.9893
   2.000   0.5328   0.01782   0.01091  -0.0673   0.8109   0.9987
   2.250   0.5512   0.01773   0.01085  -0.0658   0.7979   1.0000
   2.500   0.5648   0.01765   0.01079  -0.0634   0.7850   1.0000
   2.750   0.5785   0.01753   0.01069  -0.0609   0.7722   1.0000
   3.000   0.5925   0.01738   0.01055  -0.0583   0.7595   1.0000
   3.250   0.6076   0.01719   0.01037  -0.0557   0.7467   1.0000
   3.500   0.6219   0.01706   0.01025  -0.0530   0.7325   1.0000
   3.750   0.6395   0.01692   0.01010  -0.0507   0.7172   1.0000
   4.000   0.6583   0.01684   0.01004  -0.0487   0.6995   1.0000
   4.250   0.6805   0.01668   0.00988  -0.0470   0.6803   1.0000
   4.500   0.7058   0.01641   0.00961  -0.0457   0.6602   1.0000
   4.750   0.7285   0.01625   0.00946  -0.0440   0.6347   1.0000
   5.000   0.7518   0.01607   0.00924  -0.0424   0.6051   1.0000
   5.250   0.7748   0.01595   0.00903  -0.0406   0.5702   1.0000
   5.500   0.7954   0.01603   0.00898  -0.0388   0.5276   1.0000
   5.750   0.8153   0.01633   0.00905  -0.0369   0.4832   1.0000
   6.000   0.8345   0.01682   0.00931  -0.0352   0.4409   1.0000
   6.250   0.8537   0.01742   0.00972  -0.0337   0.4039   1.0000
   6.500   0.8728   0.01806   0.01021  -0.0322   0.3707   1.0000
   6.750   0.8918   0.01875   0.01077  -0.0308   0.3406   1.0000
   7.000   0.9101   0.01948   0.01138  -0.0294   0.3116   1.0000
   7.250   0.9274   0.02031   0.01209  -0.0279   0.2820   1.0000
   7.500   0.9429   0.02126   0.01291  -0.0262   0.2500   1.0000
   7.750   0.9564   0.02233   0.01381  -0.0242   0.2158   1.0000
   8.000   0.9692   0.02347   0.01483  -0.0221   0.1820   1.0000
   8.250   0.9832   0.02469   0.01585  -0.0202   0.1579   1.0000
   8.500   0.9995   0.02592   0.01702  -0.0187   0.1400   1.0000
   8.750   1.0188   0.02734   0.01839  -0.0176   0.1280   1.0000
   9.000   1.0410   0.02893   0.01981  -0.0171   0.1183   1.0000
   9.250   1.0606   0.03021   0.02127  -0.0160   0.1102   1.0000
   9.500   1.0864   0.03216   0.02315  -0.0160   0.1040   1.0000
   9.750   1.1076   0.03387   0.02513  -0.0152   0.0990   1.0000
  10.000   1.1314   0.03569   0.02692  -0.0150   0.0941   1.0000
  10.250   1.1506   0.03806   0.02955  -0.0142   0.0902   1.0000
  10.500   1.1655   0.04024   0.03210  -0.0127   0.0872   1.0000
  10.750   1.1807   0.04264   0.03477  -0.0114   0.0846   1.0000
  11.000   1.1951   0.04504   0.03735  -0.0103   0.0819   1.0000
  11.250   1.2072   0.04887   0.04131  -0.0095   0.0791   1.0000
  11.500   1.2009   0.05129   0.04423  -0.0061   0.0777   1.0000
  11.750   1.1914   0.05437   0.04773  -0.0029   0.0767   1.0000
  12.000   1.1761   0.05743   0.05113   0.0007   0.0760   1.0000
  12.250   1.1568   0.06072   0.05471   0.0037   0.0754   1.0000
  12.500   1.1344   0.06445   0.05871   0.0057   0.0751   1.0000
  12.750   1.1085   0.06887   0.06338   0.0066   0.0751   1.0000
  13.000   1.0794   0.07439   0.06912   0.0062   0.0759   1.0000
  13.250   1.0487   0.08074   0.07566   0.0043   0.0768   1.0000
  13.500   1.0181   0.08808   0.08315   0.0012   0.0777   1.0000
  13.750   0.9889   0.09640   0.09156  -0.0030   0.0786   1.0000
  14.000   0.9662   0.10515   0.10036  -0.0072   0.0794   1.0000
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