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Interaction of missile propulsion and aerodynamics

Published online by Cambridge University Press:  04 July 2016

C. R. Buchanan ,
A. J. T. Gemmill  and
P. G. Martin
C. R. Buchanan
Affiliation:
Weapons Propulsion and Performance Group, Propulsion Department, DERA Pyestock, UK
A. J. T. Gemmill
Affiliation:
Weapons Propulsion and Performance Group, Propulsion Department, DERA Pyestock, UK
P. G. Martin
Affiliation:
Propulsion Integration Group, Aerodynamics and Hydrodynamics Centre, DERA Bedford, UK
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Abstract

Some aspects of propulsion integration issues for ramjet powered missiles are outlined in this paper. The benefits of ramjet propulsion in the Mach 2-4 range over other types of airbreathing propulsion and rocket propulsion are well known. Compared with solid rocket motors, ramjet engines offer a much higher specific impulse and the capability of thrust management, enabling longer stand-off ranges and more flexible operation.

An overview of the ramjet engine cycle is given, highlighting engine/intake matching issues. This is followed by a performance comparison between a generic ramjet and a solid rocket powered missile (the air-to-air configuration is examined by way of example in this paper). As well as overall performance, intake integration and missile steering issues are considered.

A description of a wind tunnel test model, intake design and tunnel testing is given. The effects of design Mach number and side-wall removal have been investigated for twin ventral rectangular intake configurations. These tests were aimed at optimising performance at different flight conditions and improving tolerance to yawed flight. The impact of the alternative intake designs on missile performance is discussed.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1036 , June 2000 , pp. 271 - 277
Copyright
Copyright © Royal Aeronautical Society 2000 

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References

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