Engine sizing and integration requirements for hypersonic airbreathing missile applications
Abstract
A procedure that provides a rational means for selecting an inlet/combustor configuration for a hypersonic airbreathing missile is presented. The particular problem that is addressed is the design of the sustained engine of a two stage missile that is constrained to be launched from a stowage volume that is either square or circular in cross section. The sustainer engine accelerates from a low altitude separation at Mach 4 and climbs to high altitude for cruise at Mach 8. The results show that a missile with an axisymmetric nose inlet provides a somewhat higher thrust capability and slightly better fuel efficiency than a chin type inlet. Aft entry inlets are shown to have a substantially lower thrust potential and lower engine efficiency. A criterion for determining the maximum contraction ratio of a fixed geometry inlet is established and applied to the exemplary missile designs. Combustor area ratio is examined and found to have a relatively small effect on engine performance for area ratios equal to or larger than that required to obtain maximum thrust at the take-over Mach number.
- Publication:
-
In AGARD Ramjets and Ramrockets for Mil. Appl. 41 p (SEE N82-32256 22-99
- Pub Date:
- March 1982
- Bibcode:
- 1982rrma.agar.....W
- Keywords:
-
- Air Breathing Boosters;
- Combustion Chambers;
- Engine Inlets;
- Hypersonic Aircraft;
- Propulsion System Configurations;
- Rocket Engines;
- Descriptive Geometry;
- Engine Design;
- Engine Inlets;
- Missile Configurations;
- Nose Inlets;
- Propulsion System Performance;
- Systems Integration;
- Launch Vehicles and Space Vehicles