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HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il)
Reynolds number: 50,000
Max Cl/Cd: 25.8 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3015-il-50000.txt
Download as CSV file: xf-hq3015-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/15 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3060   0.10826   0.10164  -0.0261   1.0000   0.3563
  -9.000  -0.3332   0.10877   0.10230  -0.0227   1.0000   0.3677
  -8.750  -0.3216   0.10573   0.09928  -0.0204   1.0000   0.3817
  -8.500  -0.3203   0.10320   0.09679  -0.0181   1.0000   0.3888
  -8.250  -0.3532   0.10383   0.09760  -0.0139   1.0000   0.3998
  -8.000  -0.3341   0.09996   0.09368  -0.0126   1.0000   0.4064
  -7.750  -0.5373   0.08501   0.07931  -0.0276   1.0000   0.2044
  -7.250  -0.6501   0.06604   0.05974  -0.0361   1.0000   0.1599
  -7.000  -0.6522   0.06173   0.05521  -0.0357   1.0000   0.1591
  -6.750  -0.6518   0.05739   0.05050  -0.0355   1.0000   0.1589
  -6.500  -0.6463   0.05325   0.04589  -0.0355   1.0000   0.1591
  -6.250  -0.6365   0.04943   0.04146  -0.0356   1.0000   0.1603
  -6.000  -0.6219   0.04677   0.03870  -0.0350   1.0000   0.1645
  -5.750  -0.6055   0.04424   0.03586  -0.0345   1.0000   0.1675
  -5.500  -0.5877   0.04195   0.03314  -0.0342   1.0000   0.1724
  -5.250  -0.5682   0.03979   0.03040  -0.0339   1.0000   0.1773
  -5.000  -0.5489   0.03808   0.02867  -0.0332   1.0000   0.1824
  -4.750  -0.5283   0.03662   0.02687  -0.0326   1.0000   0.1893
  -4.500  -0.5084   0.03535   0.02550  -0.0319   1.0000   0.1984
  -4.250  -0.4872   0.03426   0.02411  -0.0312   1.0000   0.2084
  -4.000  -0.4673   0.03326   0.02318  -0.0303   1.0000   0.2207
  -3.750  -0.4473   0.03238   0.02230  -0.0294   1.0000   0.2378
  -3.500  -0.4276   0.03148   0.02154  -0.0283   1.0000   0.2592
  -3.250  -0.4080   0.03049   0.02081  -0.0273   1.0000   0.2943
  -3.000  -0.3891   0.02908   0.02027  -0.0263   1.0000   0.3725
  -2.750  -0.3849   0.02914   0.02179  -0.0197   1.0000   0.5836
  -2.500  -0.3839   0.03028   0.02302  -0.0124   1.0000   0.6735
  -2.250  -0.3817   0.03106   0.02380  -0.0057   1.0000   0.7238
  -2.000  -0.3790   0.03153   0.02422   0.0004   1.0000   0.7651
  -1.750  -0.3757   0.03174   0.02436   0.0061   1.0000   0.8031
  -1.500  -0.3722   0.03174   0.02431   0.0115   1.0000   0.8391
  -1.250  -0.3662   0.03166   0.02417   0.0162   1.0000   0.8778
  -1.000  -0.3377   0.03217   0.02460   0.0173   1.0000   0.9271
  -0.750  -0.1447   0.03712   0.02888  -0.0129   0.9924   0.9905
  -0.500  -0.0853   0.03823   0.02972  -0.0219   0.9802   1.0000
  -0.250  -0.0745   0.03819   0.02959  -0.0222   0.9726   1.0000
   0.000  -0.0640   0.03824   0.02954  -0.0223   0.9645   1.0000
   0.250  -0.0562   0.03827   0.02949  -0.0220   0.9574   1.0000
   0.500  -0.0509   0.03825   0.02938  -0.0212   0.9500   1.0000
   0.750  -0.0247   0.03909   0.03005  -0.0237   0.9397   1.0000
   1.000  -0.0114   0.03933   0.03019  -0.0239   0.9306   1.0000
   1.250   0.0199   0.04031   0.03102  -0.0269   0.9173   1.0000
   1.500   0.0540   0.04140   0.03197  -0.0301   0.9025   1.0000
   1.750   0.0890   0.04252   0.03296  -0.0333   0.8867   1.0000
   2.000   0.1243   0.04364   0.03395  -0.0362   0.8702   1.0000
   2.250   0.1595   0.04475   0.03495  -0.0390   0.8534   1.0000
   2.500   0.1945   0.04584   0.03594  -0.0415   0.8365   1.0000
   2.750   0.2297   0.04691   0.03693  -0.0438   0.8195   1.0000
   3.000   0.2628   0.04795   0.03790  -0.0458   0.8033   1.0000
   3.250   0.2952   0.04896   0.03885  -0.0475   0.7871   1.0000
   3.500   0.3267   0.04995   0.03979  -0.0490   0.7711   1.0000
   3.750   0.3574   0.05092   0.04073  -0.0502   0.7551   1.0000
   4.000   0.3878   0.05185   0.04164  -0.0513   0.7391   1.0000
   4.250   0.4178   0.05277   0.04254  -0.0522   0.7231   1.0000
   4.500   0.4488   0.05359   0.04337  -0.0531   0.7069   1.0000
   4.750   0.4784   0.05440   0.04418  -0.0537   0.6910   1.0000
   5.000   0.5092   0.05508   0.04487  -0.0543   0.6748   1.0000
   5.250   0.5388   0.05575   0.04557  -0.0546   0.6588   1.0000
   5.500   0.5690   0.05628   0.04614  -0.0548   0.6428   1.0000
   5.750   0.5976   0.05682   0.04673  -0.0548   0.6269   1.0000
   6.000   0.6266   0.05722   0.04717  -0.0547   0.6111   1.0000
   6.250   0.6538   0.05767   0.04767  -0.0543   0.5955   1.0000
   6.500   0.6803   0.05808   0.04816  -0.0539   0.5801   1.0000
   6.750   0.7036   0.05870   0.04883  -0.0532   0.5648   1.0000
   7.000   0.7264   0.05930   0.04949  -0.0525   0.5496   1.0000
   7.250   0.7467   0.06011   0.05038  -0.0516   0.5345   1.0000
   7.500   0.7657   0.06102   0.05135  -0.0508   0.5196   1.0000
   7.750   0.7831   0.06209   0.05249  -0.0498   0.5048   1.0000
   8.000   0.7971   0.06356   0.05402  -0.0489   0.4902   1.0000
   8.250   0.9296   0.05252   0.04327  -0.0486   0.4858   1.0000
   8.500   0.9474   0.05322   0.04406  -0.0472   0.4710   1.0000
   9.000   1.1116   0.04502   0.03611  -0.0511   0.4382   1.0000
   9.250   1.1382   0.04543   0.03657  -0.0503   0.4219   1.0000
   9.500   0.8799   0.07332   0.06425  -0.0439   0.4116   1.0000
   9.750   0.8520   0.08057   0.07149  -0.0446   0.3996   1.0000
  10.000   0.9264   0.07426   0.06538  -0.0415   0.3900   1.0000
  10.250   1.2443   0.04822   0.03951  -0.0479   0.3602   1.0000
  10.500   1.1789   0.05387   0.04539  -0.0403   0.3569   1.0000
  10.750   0.8864   0.09174   0.08294  -0.0436   0.3599   1.0000
  11.000   0.8214   0.10502   0.09614  -0.0480   0.3564   1.0000
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