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The estimation of aerodynamic forces on flat plate aerofoils at hypersonic and supersonic speed

Published online by Cambridge University Press:  27 January 2016

S. Punniyakotti  and
J. L. Stollery
J. L. Stollery*
Affiliation:
Cranfield University, Department of Aerospace Engineering, Bedfordshire, UK
*
[email protected]
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Abstract

Existing theories are reviewed and compared. From the Tangent Wedge formula a simple expression for the normal force on thin wings is derived and compared with some existing experimental data, which cover the whole supersonic-hypersonic range of Mach numbers.

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1185 , November 2012 , pp. 1207 - 1215
Copyright
Copyright © Royal Aeronautical Society 2012 

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References

1. Linnell, R.D. Two-dimensional airfoils in hypersonic flows, J Aero Sci, 1949, 16, pp 22–30.Google Scholar
2. Lees, L. Hypersonic flow. Proc. 5th Int. Aero. Conf. Los Angeles. Inst Aero Soc, NewYork, USA, 1955, pp 241–276.Google Scholar
3. Van Dyke, M.D. The combined supersonic-hypersonic similarity rule, J Aero Sci, 1951, 18, pp 499–500.Google Scholar
4. Collingbourne, M. An Empirical Prediction method for non-linear normal force on thinwings as supersonic speed. ARC CP 662, January 1962.Google Scholar
5. Rasmussen, M. Hypersonic flow, Wiley, 1994, New York, USA.Google Scholar
6. Busemann, A. Aerodynamic lift at supersonic speeds, Luftfahrt–Forschung, 1935, 12, (6).Google Scholar
7. Ames Research Staff. Equations, tables and charts for compressible flow, NACA TR1135, 1953.Google Scholar
8. Penland, J.A. and Armstrong, W.O. Static longitudinal aerodynamic characteristics ofseveral wing and blunt body shapes applicable for use as re-entry configurations at a Mach number of 6·8 and angles of attack up to 90°, NASA TMX 65, 1959.Google Scholar
9. McLellan, C.H., Bertram, M.H. and Moore, J.A. An investigation of four wings ofsquare plan form at a Mach number of 6·86 in the Langley 11-inch hypersonic tunnel, NACA RM L51D17, 1951.Google Scholar
10. Bertram, M.H. and McCauley, W.D. An investigation of the aerodynamic characteristics ofthin delta wings with a symmetrical double-wedge section at a Mach number of 6·9, NACA RM L55B14, 1955.Google Scholar
11. Bertram, M.H. and McCauley, W.D. Investigation of the aerodynamic characteristics at high supersonic Mach numbers of a family of delta wings having double-wedge sections with the maximum thickness at 0·18 chord, NACA RM L54G28, 1954.Google Scholar
12. Hartman, E.R. and Johnston, P.J. Mach 6 experimental and theoretical stability and performance of a cruciform missile at angles of attack up to 65°. NASA TP 2733, 1987.Google Scholar
13. Pitts, W.C. Force, moment and pressure-distribution characteristics of rectangular wings at high angles of attack and supersonic speeds. NACA RM A55K09, 1956.Google Scholar