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An inlet analysis for the NASA hypersonic research engine aerothermodynamic integration modelA theoretical analysis for the inlet of the NASA Hypersonic Research Engine (HRE) Aerothermodynamic Integration Model (AIM) has been undertaken by use of a method-of-characteristics computer program. The purpose of the analysis was to obtain pretest information on the full-scale HRE inlet in support of the experimental AIM program (completed May 1974). Mass-flow-ratio and additive-drag-coefficient schedules were obtained that well defined the range effected in the AIM tests. Mass-weighted average inlet total-pressure recovery, kinetic energy efficiency, and throat Mach numbers were obtained.
Document ID
19750002276
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Andrews, E. H., Jr. (NASA Langley Research Center Hampton, VA, United States)
Russell, J. W. (LTV Aerospace Corp. Hampton, Va., United States)
Mackley, E. A. (NASA Langley Research Center Hampton, VA, United States)
Simmonds, A. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1974
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
L-9353
NASA-TM-X-3038
Report Number: L-9353
Report Number: NASA-TM-X-3038
Accession Number
75N10348
Funding Number(s)
PROJECT: RTOP 501-24-16-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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