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The Effect of Boat-Tailing on the Flow Round a Two-Dimensional Blunt-Based Aerofoil at Zero Incidence

Published online by Cambridge University Press:  04 July 2016

D. J. Maull  and
B. J. Hoole
D. J. Maull
Affiliation:
Engineering Laboratory, Cambridge University
B. J. Hoole
Affiliation:
Engineering Laboratory, Cambridge University
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Summary

Some experiments on the effect of boat-tailing on the pressure distribution round blunt-based aerofoils are described. The experiments were carried out at low speeds at a Reynolds number of 1.5 X 105. The wake was investigated with attention being paid to the vortex shedding, and to the distance downstream of the base where vortices form.

It is shown that the theory due to Nash predicts the effect of boat-tailing on base pressure quite well and that a correlation of drag coefficient, Strouhal number and base pressure proposed by Bearman applies to the models tested here.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 71 , Issue 684 , December 1967 , pp. 854 - 858
Copyright
Copyright © Royal Aeronautical Society 1967

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References

1.Bearman, P. W. A Study of Unsteady Base Flows. PhD Dissertation, Cambridge University, 1965.Google Scholar
2.Bearman, P. W.Investigation of the Flow Behind a Two-Dimensional Model with a Blunt Trailing Edge and Fitted with Splitter Plates. J Fluid Mech, Vol 21, Pt 2, p 241, 1965.Google Scholar
3.Bellhouse, B. J. and Wood, C. J.The Upstream Influence of Base Bleed on Surface Pressures and Skin Friction. Journal of the Royal Aeronautical Society, Vol 69, p 789, 1965.Google Scholar
4.Maull, D. J.The Pressure Distribution at Low Speeds on Two-Dimensional Aerofoils with Blunt Trailing Edges at Zero Incidence. Journal of the Royal Aeronautical Society, Vol 70, p 727, 1966.Google Scholar
5.Nash, J. F. An Approximate Method for the Prediction of the Zero Lift Pressure Distribution and Drag of Symmetrical Blunt Trailing Edge Aerofoil Sections at Subsonic Speeds in the Absence of a Vortex Street. Aero Res Coun R & M 3436, 1964.Google Scholar
6.Pankhurst, R. C. and Holder, D. W.Wind Tunnel Techniques, Pitman, 1952.Google Scholar
7.Smith, H. A. and Schaeffer, R. F. Aerodynamic Characteristics at Reynolds Numbers of 3.0 X 106 and 6.0 X 106 of Three Airfoil Sections Formed by Cutting off Various Amounts from the Rear Portion of the NACA 0012 Airfoil Section. NACA TN 2074, 1950.Google Scholar