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HQ 3.5/18 AIRFOIL (hq3518-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/18 AIRFOIL (hq3518-il)
Reynolds number: 50,000
Max Cl/Cd: 6.95 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3518-il-50000.txt
Download as CSV file: xf-hq3518-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/18 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3786   0.12548   0.11922  -0.0104   1.0000   0.3714
  -8.750  -0.3607   0.12164   0.11537  -0.0093   1.0000   0.3765
  -8.500  -0.6196   0.09265   0.08667  -0.0317   1.0000   0.1935
  -8.250  -0.5855   0.09183   0.08587  -0.0286   1.0000   0.1976
  -8.000  -0.7222   0.07684   0.07050  -0.0335   1.0000   0.1764
  -7.750  -0.7292   0.07255   0.06610  -0.0326   1.0000   0.1749
  -7.500  -0.7387   0.06791   0.06121  -0.0322   1.0000   0.1737
  -7.250  -0.7442   0.06337   0.05633  -0.0320   1.0000   0.1734
  -7.000  -0.7438   0.05919   0.05173  -0.0318   1.0000   0.1738
  -6.750  -0.7377   0.05546   0.04752  -0.0318   1.0000   0.1745
  -6.500  -0.7269   0.05223   0.04379  -0.0316   1.0000   0.1757
  -6.250  -0.7134   0.04948   0.04064  -0.0314   1.0000   0.1784
  -6.000  -0.6972   0.04785   0.03906  -0.0305   1.0000   0.1829
  -5.750  -0.6803   0.04598   0.03691  -0.0300   1.0000   0.1871
  -5.500  -0.6621   0.04417   0.03464  -0.0297   1.0000   0.1921
  -5.250  -0.6439   0.04260   0.03294  -0.0292   1.0000   0.1979
  -5.000  -0.6251   0.04142   0.03168  -0.0285   1.0000   0.2047
  -4.750  -0.6053   0.04022   0.03015  -0.0280   1.0000   0.2127
  -4.500  -0.5867   0.03928   0.02931  -0.0272   1.0000   0.2221
  -4.250  -0.5671   0.03838   0.02833  -0.0265   1.0000   0.2325
  -4.000  -0.5477   0.03772   0.02759  -0.0258   1.0000   0.2460
  -3.750  -0.5291   0.03707   0.02709  -0.0248   1.0000   0.2615
  -3.500  -0.5104   0.03644   0.02658  -0.0239   1.0000   0.2829
  -3.250  -0.4923   0.03564   0.02608  -0.0229   1.0000   0.3154
  -3.000  -0.4764   0.03452   0.02595  -0.0214   1.0000   0.3840
  -2.750  -0.4699   0.03516   0.02773  -0.0159   1.0000   0.5478
  -2.500  -0.4663   0.03684   0.02958  -0.0093   1.0000   0.6215
  -2.250  -0.4618   0.03819   0.03094  -0.0033   1.0000   0.6640
  -2.000  -0.4570   0.03918   0.03188   0.0021   1.0000   0.6993
  -1.750  -0.4511   0.03989   0.03251   0.0068   1.0000   0.7307
  -1.500  -0.4469   0.04042   0.03300   0.0119   1.0000   0.7570
  -1.250  -0.4420   0.04080   0.03330   0.0164   1.0000   0.7849
  -1.000  -0.4382   0.04104   0.03350   0.0213   1.0000   0.8112
  -0.750  -0.4330   0.04119   0.03358   0.0255   1.0000   0.8380
  -0.500  -0.4263   0.04130   0.03361   0.0294   1.0000   0.8638
  -0.250  -0.4155   0.04150   0.03376   0.0323   1.0000   0.8907
   0.000  -0.3934   0.04216   0.03434   0.0327   1.0000   0.9194
   0.250  -0.3329   0.04445   0.03648   0.0255   1.0000   0.9485
   0.500  -0.2492   0.04770   0.03952   0.0127   1.0000   0.9693
   0.750  -0.1712   0.05068   0.04232   0.0001   1.0000   0.9899
   1.000  -0.1433   0.05172   0.04325  -0.0037   1.0000   1.0000
   1.250  -0.1271   0.05226   0.04372  -0.0054   0.9936   1.0000
   1.500  -0.0961   0.05357   0.04494  -0.0096   0.9772   1.0000
   1.750  -0.0735   0.05438   0.04567  -0.0121   0.9597   1.0000
   2.000  -0.0572   0.05499   0.04621  -0.0133   0.9438   1.0000
   2.250  -0.0425   0.05552   0.04667  -0.0141   0.9278   1.0000
   2.500  -0.0256   0.05626   0.04732  -0.0153   0.9120   1.0000
   2.750  -0.0026   0.05741   0.04838  -0.0174   0.8957   1.0000
   3.000   0.0242   0.05886   0.04974  -0.0200   0.8787   1.0000
   3.250   0.0518   0.06048   0.05127  -0.0228   0.8619   1.0000
   3.500   0.0820   0.06225   0.05297  -0.0258   0.8433   1.0000
   3.750   0.1508   0.06503   0.05558  -0.0325   0.8014   1.0000
   4.000   0.1596   0.06680   0.05733  -0.0334   0.8007   1.0000
   4.250   0.2512   0.06453   0.05482  -0.0367   0.7076   1.0000
   4.500   0.2821   0.06577   0.05600  -0.0386   0.6914   1.0000
   4.750   0.3176   0.06700   0.05717  -0.0407   0.6764   1.0000
   5.000   0.3411   0.06840   0.05853  -0.0418   0.6634   1.0000
   5.250   0.3478   0.07028   0.06038  -0.0418   0.6521   1.0000
   5.500   0.3763   0.07175   0.06181  -0.0432   0.6397   1.0000
   5.750   0.4106   0.07303   0.06305  -0.0448   0.6277   1.0000
   6.000   0.4065   0.07540   0.06542  -0.0442   0.6183   1.0000
   6.250   0.4385   0.07680   0.06678  -0.0455   0.6067   1.0000
   6.500   0.4567   0.07839   0.06837  -0.0459   0.5951   1.0000
   6.750   0.4631   0.08047   0.07044  -0.0457   0.5838   1.0000
   7.000   0.4890   0.08171   0.07167  -0.0462   0.5703   1.0000
   7.250   0.5263   0.08235   0.07230  -0.0470   0.5569   1.0000
   7.500   0.5345   0.08434   0.07430  -0.0469   0.5448   1.0000
   7.750   0.5411   0.08659   0.07657  -0.0467   0.5331   1.0000
   8.000   0.5664   0.08783   0.07782  -0.0470   0.5207   1.0000
   8.250   0.6094   0.08785   0.07786  -0.0474   0.5085   1.0000
   8.500   0.5942   0.09169   0.08173  -0.0470   0.4966   1.0000
   8.750   0.6066   0.09390   0.08397  -0.0471   0.4851   1.0000
   9.000   0.6469   0.09398   0.08408  -0.0471   0.4731   1.0000
   9.250   0.6391   0.09771   0.08785  -0.0472   0.4612   1.0000
   9.500   0.6418   0.10094   0.09111  -0.0474   0.4506   1.0000
   9.750   0.6940   0.09990   0.09012  -0.0470   0.4395   1.0000
  10.000   0.6538   0.10712   0.09737  -0.0480   0.4311   1.0000
  10.250   0.6888   0.10770   0.09799  -0.0478   0.4204   1.0000
  10.500   0.6643   0.11407   0.10441  -0.0493   0.4165   1.0000
  10.750   0.6563   0.11894   0.10932  -0.0505   0.4142   1.0000
  11.000   0.6522   0.12354   0.11396  -0.0518   0.4132   1.0000
  11.250   0.6521   0.12870   0.11917  -0.0536   0.4184   1.0000
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