Accession Number : ADP007956
Title : Performance Characteristics of Hypersonic Detonation Wave Ramjets,
Corporate Author : TORONTO UNIV DOWNSVIEW (ONTARIO) INST FOR AEROSPACE STUDIES
Personal Author(s) : Atamanchuk, T. M. ; Sislian, J. P.
Report Date : DEC 1990
Pagination or Media Count : 13
Abstract : One method of heat addition to a supersonic flow is by means of shock-induced combustion or in this particular study a detonation wave. In order to assess the performance potential of a propulsor utilizing such a mode of heat addition a first order inviscid computational scheme based on Godunov's method was developed. This computational method was chosen since it allows one to track flow-field discontinuities such as shocks and slipstreams, thus making it possible to generate a vehicle geometry operating at design conditions for given freestream conditions. This same code was also used to determine the flow-field generated by a given body geometry at off-design conditions. Pressures acting on these planar and axisymmetric bodies were calculated and used to determine various performance parameters over a range of Mach numbers.
Descriptors : *DETONATION WAVES, *SUPERSONIC FLOW, *HYPERSONIC FLOW, *RAMJET ENGINES, ADDITION, AXISYMMETRIC, BODIES, COMBUSTION, DETONATIONS, DISCONTINUITIES, FLOW, FLOW FIELDS, GEOMETRY, HEAT, MACH NUMBER, NUMBERS, PARAMETERS, PRESSURE, SHOCK, TRACKS, VEHICLES.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE