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Control of plume interference effects on axisymmetric afterbodies

Published online by Cambridge University Press:  03 February 2016

Y-K Lee ,
S. Raghunathan ,
E. Benard ,
H-D Kim  and
T. Setoguchi
Y-K Lee
Affiliation:
School of Aeronautical Engineering, Queen’s University of Belfast, Belfast UK
S. Raghunathan
Affiliation:
School of Aeronautical Engineering, Queen’s University of Belfast, Belfast UK
E. Benard
Affiliation:
School of Aeronautical Engineering, Queen’s University of Belfast, Belfast UK
H-D Kim
Affiliation:
School of Mechanical Engineering, Andong National University, Andong, Korea
T. Setoguchi
Affiliation:
Department of Mechanical Engineering, Saga University, Saga, Japan
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Abstract

Plume interference effects on the axisymmetric flowfields around powered missiles are investigated using computational techniques. The study is mainly to understand the physics of the plume-induced shock and separation particularly at high plume to exit pressure ratios with and without shock-turbulent boundary layer control methods. Mass-averaged Navier-Stokes equations with the RNG k-ε turbulence model are solved using a fully implicit finite volume scheme and time-marching algorithm. The shock position and extent of separation was found to be dependent on the freestream Mach number and plume pressure ratio. Rounding the tail or a groove on the surface near the tail moved the shockwave downstream of the tail fin which should enhance the control of the missile.

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1082 , April 2004 , pp. 185 - 196
Copyright
Copyright © Royal Aeronautical Society 2004 

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