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HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il)
Reynolds number: 100,000
Max Cl/Cd: 56.85 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3513-il-100000.txt
Download as CSV file: xf-hq3513-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/13 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3317   0.10195   0.09810  -0.0274   1.0000   0.1156
  -8.500  -0.3637   0.09989   0.09614  -0.0284   1.0000   0.1179
  -8.250  -0.3976   0.09775   0.09410  -0.0293   1.0000   0.1185
  -8.000  -0.3736   0.09375   0.09011  -0.0257   0.9996   0.1214
  -7.750  -0.3544   0.08989   0.08622  -0.0271   0.9959   0.1272
  -7.500  -0.3805   0.08485   0.08125  -0.0338   0.9898   0.1326
  -7.250  -0.5141   0.08776   0.08403  -0.0312   0.9992   0.1203
  -7.000  -0.4828   0.08680   0.08306  -0.0251   0.9970   0.1256
  -6.750  -0.4916   0.07681   0.07287  -0.0453   0.9857   0.1349
  -6.500  -0.4618   0.07485   0.07102  -0.0422   0.9832   0.1400
  -6.250  -0.4583   0.06878   0.06477  -0.0502   0.9745   0.1514
  -6.000  -0.4412   0.04912   0.04344  -0.0647   0.9684   0.0772
  -5.750  -0.4193   0.04475   0.03878  -0.0656   0.9630   0.0709
  -5.500  -0.3891   0.04043   0.03383  -0.0682   0.9584   0.0705
  -5.250  -0.3549   0.03712   0.02981  -0.0704   0.9546   0.0730
  -5.000  -0.3297   0.03472   0.02676  -0.0703   0.9490   0.0748
  -4.750  -0.2980   0.03250   0.02444  -0.0721   0.9445   0.0826
  -4.500  -0.2589   0.03070   0.02223  -0.0744   0.9411   0.0932
  -4.250  -0.2371   0.03000   0.02132  -0.0737   0.9346   0.1024
  -4.000  -0.2042   0.02873   0.02001  -0.0750   0.9298   0.1124
  -3.750  -0.1642   0.02771   0.01886  -0.0772   0.9263   0.1223
  -3.500  -0.1448   0.02720   0.01832  -0.0759   0.9193   0.1310
  -3.250  -0.1114   0.02645   0.01767  -0.0771   0.9144   0.1439
  -3.000  -0.0763   0.02586   0.01716  -0.0785   0.9100   0.1627
  -2.750  -0.0566   0.02533   0.01684  -0.0776   0.9027   0.1908
  -2.500  -0.0290   0.02338   0.01686  -0.0780   0.8984   0.5462
  -2.250  -0.0133   0.02399   0.01763  -0.0746   0.8913   0.6571
  -2.000   0.0094   0.02451   0.01813  -0.0726   0.8846   0.7054
  -1.750   0.0331   0.02494   0.01851  -0.0709   0.8786   0.7403
  -1.500   0.0499   0.02524   0.01878  -0.0683   0.8707   0.7676
  -1.000   0.0853   0.02560   0.01910  -0.0629   0.8566   0.8254
  -0.750   0.1066   0.02548   0.01899  -0.0598   0.8516   0.8661
  -0.500   0.1090   0.02552   0.01907  -0.0547   0.8421   0.8994
  -0.250   0.1491   0.02540   0.01891  -0.0560   0.8374   0.9310
   0.000   0.1888   0.02566   0.01910  -0.0591   0.8297   0.9523
   0.250   0.2482   0.02574   0.01906  -0.0654   0.8244   0.9693
   0.500   0.3173   0.02560   0.01879  -0.0731   0.8213   0.9838
   0.750   0.3379   0.02579   0.01891  -0.0735   0.8098   1.0000
   1.000   0.3967   0.02517   0.01817  -0.0784   0.8049   1.0000
   1.250   0.4231   0.02502   0.01795  -0.0787   0.7934   1.0000
   1.500   0.4565   0.02478   0.01764  -0.0798   0.7826   1.0000
   1.750   0.5132   0.02386   0.01664  -0.0839   0.7778   1.0000
   2.000   0.5394   0.02394   0.01668  -0.0841   0.7671   1.0000
   2.250   0.5887   0.02321   0.01590  -0.0870   0.7628   1.0000
   2.500   0.6142   0.02332   0.01599  -0.0869   0.7519   1.0000
   2.750   0.6624   0.02251   0.01515  -0.0895   0.7473   1.0000
   3.000   0.6884   0.02253   0.01516  -0.0892   0.7360   1.0000
   3.250   0.7370   0.02159   0.01418  -0.0916   0.7312   1.0000
   3.500   0.7626   0.02154   0.01415  -0.0910   0.7189   1.0000
   3.750   0.7922   0.02132   0.01393  -0.0908   0.7076   1.0000
   4.000   0.8313   0.02068   0.01327  -0.0919   0.6986   1.0000
   4.250   0.8666   0.02014   0.01275  -0.0923   0.6871   1.0000
   4.500   0.8960   0.01984   0.01245  -0.0920   0.6730   1.0000
   4.750   0.9265   0.01949   0.01209  -0.0917   0.6580   1.0000
   5.000   0.9577   0.01911   0.01170  -0.0915   0.6416   1.0000
   5.250   0.9809   0.01901   0.01162  -0.0902   0.6206   1.0000
   5.500   1.0088   0.01875   0.01131  -0.0895   0.5986   1.0000
   5.750   1.0322   0.01870   0.01122  -0.0882   0.5721   1.0000
   6.000   1.0556   0.01873   0.01115  -0.0869   0.5430   1.0000
   6.250   1.0779   0.01896   0.01122  -0.0855   0.5127   1.0000
   6.500   1.0994   0.01939   0.01146  -0.0842   0.4838   1.0000
   6.750   1.1214   0.01995   0.01185  -0.0831   0.4584   1.0000
   7.000   1.1428   0.02060   0.01236  -0.0821   0.4360   1.0000
   7.250   1.1664   0.02130   0.01290  -0.0815   0.4173   1.0000
   7.500   1.1876   0.02203   0.01358  -0.0805   0.3999   1.0000
   7.750   1.2097   0.02278   0.01430  -0.0797   0.3845   1.0000
   8.000   1.2319   0.02354   0.01502  -0.0790   0.3701   1.0000
   8.250   1.2545   0.02432   0.01575  -0.0783   0.3565   1.0000
   8.500   1.2750   0.02508   0.01653  -0.0774   0.3432   1.0000
   8.750   1.2939   0.02586   0.01740  -0.0762   0.3302   1.0000
   9.000   1.3126   0.02668   0.01827  -0.0749   0.3176   1.0000
   9.250   1.3319   0.02756   0.01919  -0.0739   0.3055   1.0000
   9.500   1.3518   0.02848   0.02012  -0.0729   0.2935   1.0000
   9.750   1.3732   0.02946   0.02108  -0.0722   0.2814   1.0000
  10.000   1.3910   0.03042   0.02207  -0.0710   0.2691   1.0000
  10.250   1.4031   0.03142   0.02325  -0.0689   0.2573   1.0000
  10.500   1.4168   0.03250   0.02443  -0.0671   0.2456   1.0000
  10.750   1.4311   0.03354   0.02550  -0.0654   0.2340   1.0000
  11.000   1.4460   0.03450   0.02643  -0.0639   0.2223   1.0000
  11.250   1.4467   0.03541   0.02758  -0.0602   0.2122   1.0000
  11.500   1.4494   0.03645   0.02875  -0.0569   0.2023   1.0000
  11.750   1.4568   0.03738   0.02965  -0.0545   0.1924   1.0000
  12.000   1.4543   0.03846   0.03088  -0.0509   0.1833   1.0000
  12.250   1.4527   0.03975   0.03231  -0.0478   0.1742   1.0000
  12.500   1.4562   0.04085   0.03335  -0.0455   0.1651   1.0000
  12.750   1.4489   0.04245   0.03518  -0.0424   0.1566   1.0000
  13.000   1.4451   0.04413   0.03693  -0.0400   0.1481   1.0000
  13.250   1.4431   0.04570   0.03843  -0.0381   0.1394   1.0000
  13.500   1.4327   0.04810   0.04109  -0.0359   0.1311   1.0000
  13.750   1.4261   0.05041   0.04341  -0.0344   0.1229   1.0000
  14.000   1.4171   0.05304   0.04615  -0.0332   0.1147   1.0000
  14.250   1.4069   0.05621   0.04948  -0.0323   0.1067   1.0000
  14.500   1.3986   0.05931   0.05251  -0.0317   0.0990   1.0000
  14.750   1.3860   0.06325   0.05669  -0.0316   0.0916   1.0000
  15.000   1.3759   0.06721   0.06070  -0.0316   0.0844   1.0000
  15.250   1.3638   0.07160   0.06517  -0.0321   0.0776   1.0000
  15.500   1.3505   0.07654   0.07024  -0.0329   0.0709   1.0000
  15.750   1.3387   0.08131   0.07496  -0.0340   0.0647   1.0000
  16.000   1.3239   0.08707   0.08095  -0.0356   0.0594   1.0000
  16.250   1.3138   0.09205   0.08590  -0.0371   0.0545   1.0000
  16.500   1.3028   0.09759   0.09161  -0.0388   0.0506   1.0000
  16.750   1.2925   0.10317   0.09735  -0.0409   0.0473   1.0000
  17.000   1.2962   0.10605   0.10005  -0.0408   0.0433   1.0000
  17.250   1.2838   0.11234   0.10665  -0.0436   0.0421   1.0000
  17.500   1.2715   0.11877   0.11334  -0.0467   0.0410   1.0000
  17.750   1.2579   0.12564   0.12045  -0.0502   0.0402   1.0000
  18.000   1.2429   0.13304   0.12807  -0.0544   0.0398   1.0000
  18.250   1.2236   0.14169   0.13694  -0.0597   0.0398   1.0000
  18.500   1.1969   0.15256   0.14805  -0.0668   0.0405   1.0000
  18.750   1.1642   0.16567   0.16134  -0.0755   0.0418   1.0000
  19.000   1.1319   0.17972   0.17547  -0.0846   0.0431   1.0000
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