OPTIMIZATION OF A SCRAMJET CONFIGURATION.

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Abstract:

The configuration optimization study was conducted to analytically determine the two dimensional cruise configuration of a Mach ten hydrogen-fueled scramjet vehicle that provided maximum cruise range. Two combustion processes, constant area and constant pressure, and three configuration variables inlet compression angle, nozzle expansion angle, and the angle of the top surface of the vehicle relative to the direction of flight were considered. A computerized open loop search for the optimum configuration was conducted. Within the constraints of the problem, the vehicle with constant area combustion had a better cruise range than the vehicle with constant pressure combustion. Author

Author(s):
Williams, John Edward
Author Organization(s):
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Descriptive Note:
Master's thesis,
Pagination:
0054

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
GAM/ME/67-18
 Subject Terms
Modernization Areas:
Hypersonics
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*SUPERSONIC COMBUSTION RAMJET ENGINES, RAMJET ENGINES, COMBUSTION, HYPERSONIC FLOW, SUPERSONIC FLOW, STRATOSPHERE, RAMJET ENGINE NOZZLES, COMPATIBILITY, PERFORMANCE(ENGINEERING), RANGE(DISTANCE), JET ENGINE INLETS, MATHEMATICAL MODELS, OPTIMIZATION, THESES, HYDROGEN, CONFIGURATIONS
Field(s)/Group(s):
Fluid Mechanics, Combustion and Ignition, Jet and Gas Turbine Engines
Report Date:
1967 Jun 01