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HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il)
Reynolds number: 50,000
Max Cl/Cd: 29.41 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3514-il-50000.txt
Download as CSV file: xf-hq3514-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/14 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3405   0.11648   0.10996  -0.0296   1.0000   0.3032
  -9.250  -0.3133   0.11136   0.10481  -0.0277   1.0000   0.3141
  -9.000  -0.3311   0.11038   0.10396  -0.0252   1.0000   0.3221
  -8.750  -0.3369   0.10907   0.10272  -0.0223   1.0000   0.3342
  -8.500  -0.3302   0.10625   0.09994  -0.0199   1.0000   0.3456
  -8.250  -0.3409   0.10487   0.09865  -0.0170   1.0000   0.3568
  -8.000  -0.3749   0.10580   0.09975  -0.0131   1.0000   0.3682
  -7.750  -0.3706   0.10341   0.09740  -0.0104   1.0000   0.3833
  -7.500  -0.3628   0.10072   0.09473  -0.0080   1.0000   0.3970
  -7.250  -0.3608   0.09846   0.09251  -0.0056   1.0000   0.4093
  -7.000  -0.3649   0.09682   0.09093  -0.0027   1.0000   0.4243
  -6.750  -0.3704   0.09537   0.08952   0.0004   1.0000   0.4411
  -6.500  -0.3781   0.09404   0.08827   0.0037   1.0000   0.4582
  -6.000  -0.5711   0.06292   0.05670  -0.0354   1.0000   0.1789
  -5.750  -0.5598   0.05754   0.05090  -0.0378   1.0000   0.1707
  -5.500  -0.5437   0.05174   0.04441  -0.0411   1.0000   0.1639
  -5.250  -0.5218   0.04753   0.03939  -0.0430   1.0000   0.1596
  -5.000  -0.4995   0.04451   0.03569  -0.0440   1.0000   0.1608
  -4.750  -0.4803   0.04224   0.03344  -0.0437   1.0000   0.1647
  -4.500  -0.4577   0.04009   0.03093  -0.0438   1.0000   0.1669
  -4.250  -0.4345   0.03837   0.02881  -0.0438   1.0000   0.1718
  -4.000  -0.4110   0.03679   0.02684  -0.0437   1.0000   0.1778
  -3.750  -0.3892   0.03550   0.02546  -0.0432   1.0000   0.1837
  -3.500  -0.3662   0.03448   0.02412  -0.0429   1.0000   0.1930
  -3.250  -0.3449   0.03354   0.02319  -0.0421   1.0000   0.2033
  -3.000  -0.3235   0.03269   0.02234  -0.0413   1.0000   0.2151
  -2.750  -0.3025   0.03199   0.02169  -0.0405   1.0000   0.2323
  -2.500  -0.2813   0.03139   0.02112  -0.0396   1.0000   0.2538
  -2.250  -0.2586   0.03063   0.02066  -0.0394   1.0000   0.2938
  -2.000  -0.2414   0.02917   0.02133  -0.0366   1.0000   0.5638
  -1.750  -0.2473   0.03013   0.02260  -0.0270   1.0000   0.7172
  -1.500  -0.2488   0.03056   0.02304  -0.0195   1.0000   0.7773
  -1.250  -0.2482   0.03069   0.02313  -0.0132   1.0000   0.8256
  -1.000  -0.2450   0.03063   0.02305  -0.0077   1.0000   0.8705
  -0.750  -0.2275   0.03065   0.02309  -0.0050   1.0000   0.9338
  -0.500  -0.1736   0.03124   0.02347  -0.0119   1.0000   1.0000
  -0.250  -0.1614   0.03123   0.02326  -0.0122   1.0000   1.0000
   0.000  -0.1430   0.03156   0.02340  -0.0136   1.0000   1.0000
   0.250  -0.0778   0.03390   0.02537  -0.0232   0.9793   1.0000
   0.500  -0.0333   0.03535   0.02657  -0.0289   0.9646   1.0000
   0.750   0.0087   0.03674   0.02775  -0.0338   0.9502   1.0000
   1.000   0.0487   0.03813   0.02893  -0.0383   0.9371   1.0000
   1.250   0.0895   0.03961   0.03023  -0.0427   0.9243   1.0000
   1.500   0.1266   0.04078   0.03123  -0.0461   0.9076   1.0000
   1.750   0.1660   0.04184   0.03215  -0.0496   0.8868   1.0000
   2.000   0.2169   0.04309   0.03324  -0.0542   0.8657   1.0000
   2.250   0.2590   0.04418   0.03421  -0.0575   0.8479   1.0000
   2.500   0.2949   0.04520   0.03514  -0.0599   0.8325   1.0000
   2.750   0.3252   0.04616   0.03603  -0.0614   0.8179   1.0000
   3.000   0.3528   0.04712   0.03693  -0.0625   0.8032   1.0000
   3.250   0.3806   0.04810   0.03787  -0.0636   0.7886   1.0000
   3.500   0.4085   0.04908   0.03882  -0.0646   0.7739   1.0000
   3.750   0.4366   0.05007   0.03978  -0.0655   0.7590   1.0000
   4.000   0.4641   0.05106   0.04076  -0.0663   0.7441   1.0000
   4.250   0.4924   0.05201   0.04172  -0.0670   0.7287   1.0000
   4.500   0.5207   0.05294   0.04266  -0.0676   0.7131   1.0000
   4.750   0.5472   0.05393   0.04367  -0.0681   0.6977   1.0000
   5.000   0.5738   0.05489   0.04467  -0.0684   0.6820   1.0000
   5.250   0.6001   0.05582   0.04563  -0.0687   0.6663   1.0000
   5.500   0.6255   0.05676   0.04662  -0.0688   0.6507   1.0000
   5.750   0.6571   0.05710   0.04702  -0.0688   0.6339   1.0000
   6.000   0.6938   0.05685   0.04683  -0.0688   0.6169   1.0000
   6.250   0.7317   0.05629   0.04636  -0.0686   0.6004   1.0000
   6.500   0.7634   0.05613   0.04628  -0.0681   0.5847   1.0000
   6.750   0.7923   0.05610   0.04634  -0.0675   0.5694   1.0000
   7.000   0.8213   0.05599   0.04635  -0.0667   0.5543   1.0000
   7.250   0.8510   0.05569   0.04614  -0.0657   0.5394   1.0000
   7.500   0.8837   0.05491   0.04549  -0.0646   0.5247   1.0000
   7.750   0.9204   0.05355   0.04427  -0.0634   0.5105   1.0000
   8.000   0.9800   0.04991   0.04080  -0.0626   0.4971   1.0000
   8.250   1.0963   0.04274   0.03385  -0.0662   0.4797   1.0000
   8.500   1.1748   0.03995   0.03106  -0.0694   0.4565   1.0000
   8.750   1.1948   0.04101   0.03217  -0.0681   0.4369   1.0000
   9.000   1.2196   0.04201   0.03320  -0.0673   0.4184   1.0000
   9.250   1.2401   0.04330   0.03457  -0.0663   0.4018   1.0000
   9.500   1.2549   0.04498   0.03634  -0.0648   0.3877   1.0000
   9.750   1.2734   0.04658   0.03802  -0.0638   0.3753   1.0000
  10.000   1.3012   0.04768   0.03917  -0.0636   0.3626   1.0000
  10.250   1.2711   0.05150   0.04325  -0.0584   0.3556   1.0000
  10.500   1.2902   0.05313   0.04498  -0.0576   0.3456   1.0000
  10.750   1.2226   0.05970   0.05171  -0.0511   0.3434   1.0000
  11.000   0.9487   0.09820   0.08975  -0.0580   0.3477   1.0000
  11.250   0.8995   0.11008   0.10157  -0.0623   0.3462   1.0000
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