Accession Number : ADA192845
Title : Variable Mach Number Wall Jets for Control/Propulsion on Hypervelocity Projectiles/Interceptors: Tests with an Existing Model.
Descriptive Note : Final rept. 22 Jul 87-21 Jan 88,
Corporate Author : HOKENSON CO LOS ANGELES CA
Personal Author(s) : Hokenson, Gustave J
PDF Url : ADA192845
Report Date : Jan 1988
Pagination or Media Count : 19
Abstract : Wind tunnel tests, utilizing a one-sixth scale model of a proposed interceptor configuration, were carried out to assess the feasibility of variable Mach number wall jets for propulsion and control applications at high altitude. The objective of this preliminary study was to assess the performance of such a thruster at high altitude where an enormous billowing of underexpanded exhaust plumes may cause a variety of problems. Included in these is sensor obscuration as a result of the upstream migration of low momentum nozzle boundary layer contaminants. The partially-bounded nature of the wall jet configuration, as well as its variable Mach number capabilities favorably impact this problem. In addition, the configuration admits a simple staging, wherein the nose may explosively separate separate from the afterbody prior to impact for damage enhancement. The tests indicated that no degradation in thrust is inherent to the configuration. Additional flowfield visualizations are required to quantify the obscuration problem at highly underexpanded conditions. Subsequent tests shall also assess the generation of control sideforces with an asymmetric nozzle throat.
Descriptors : *HYPERVELOCITY PROJECTILES, *THRUSTERS, *JET FLOW, *ROCKET EXHAUST, AFTERBODIES, ASYMMETRY, CONFIGURATIONS, CONTROL, DAMAGE, DETECTORS, HIGH ALTITUDE, INTERCEPTORS, MACH NUMBER, MIGRATION, NOSES, NOZZLE THROATS, OBSCURATION, OPTIMIZATION, PROPULSION SYSTEMS, STAGING, WIND TUNNEL TESTS, EXHAUST NOZZLES, WALLS, THRUST, JET PROPULSION, ANGLE OF ATTACK, EXHAUST PLUMES, WIND TUNNEL MODELS
Subject Categories : Ammunition and Explosives
Distribution Statement : APPROVED FOR PUBLIC RELEASE