Accession Number:

ADP007956

Title:

Performance Characteristics of Hypersonic Detonation Wave Ramjets,

Descriptive Note:

Corporate Author:

TORONTO UNIV DOWNSVIEW (ONTARIO) INST FOR AEROSPACE STUDIES

Personal Author(s):

• Atamanchuk, T. M.
• Sislian, J. P.

Report Date:

1990-12-01

Pagination or Media Count:

13.0

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 Godunovs 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