Interaction of missile propulsion and aerodynamics

Some aspects of propulsion integration issues for ramjet powered missiles a re outlined in this paper. The benefits of ramjet propulsion in the Mach 2- 4 range over other types of airbreathing propulsion and rocket propulsion a re well known. Compared with solid rocket motors, ramjet engines offer a mu ch higher specific impulse and the capability of thrust management, enablin g 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 ge neric ramjet and a solid rocket powered missile (the air-to-air configurati on is examined by way of example in this paper). As well as over all perfor mance, 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 sidewall removal have been investigated for twin ventral rectangular intake configurations. These tes ts were aimed at optimising performance at different flight conditions and improving tolerance to yawed flight. The impact of the alternative intake d esigns on missile performance is discussed.