Accession Number:

ADA172711

Title:

Pressure Interactions in Supersonic Combustion.

Descriptive Note:

Final rept. 1 Jun 84-28 Feb 86,

Corporate Author:

SCIENCE APPLICATIONS INTERNATIONAL CORP CHATSWORTH CA COMBUSTION SCIENCE AND ADVANCED TECHNOLOGY DEPT

Personal Author(s):

• Edelman,R. B.
• Bragg,W. N.

Report Date:

1986-06-11

Pagination or Media Count:

58.0

Abstract:

A detailed assessment of supersonic combustion was carried out to identify specific research requirements in modeling turbulent reacting supersonic flows. The direct effects of pressure gradients and pressure fluctuations on turbulence were found to be potentially responsible for certain of the trends in turbulent transport and mixing rates that are observed in supersonic flows. An approach to the modeling of these phenomena is delineated, A modular model computer code for the analysis of sudden expansion dump combustors was prepared. This modular model is designed to be used parametrically in evaluating effects such as chemical kinetics limitation on flame stabilization and combustion efficiency in integral rocket ramjet and ducted rocket combustors. Keywords Pressure Interactions, Turbulence modeling, Sudden expansion combustors, Dump combustors.

Descriptors:

• *TURBULENT FLOW
• *COMBUSTORS
• *SUPERSONIC COMBUSTION
• STABILIZATION
• PRESSURE GRADIENTS
• COMPUTER PROGRAMS
• REACTION KINETICS
• INTERACTIONS
• RATES
• EFFICIENCY
• MODULAR CONSTRUCTION
• VARIATIONS
• TRANSPORT PROPERTIES
• PRESSURE
• MIXING
• FLAMES
• FLAME PROPAGATION
• SUPERSONIC FLOW
• FUEL INJECTION
• INTEGRAL ROCKET RAMJETS
• DUCTED ROCKETS

Subject Categories:

• Air Breathing Engines (Unconventional)
• Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE