NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Internal shock interactions in propulsion/airframe integrated three-dimensional sidewall compression scramjet inletsThe advantages and design requirements of propulsion/airframe integration for high Mach number flight are studied in terms of the 3D sidewall compression scramjet inlet. The present work addresses in a parametric fashion the inviscid effects of leading edge sweep, sidewall compression, and inflow Mach number on the internal shock structure in terms of inlet compression and mass capture. The source of the Mach number invariance with leading edge sweep for a constant sidewall compression class of inlet is identified, and a previously undocumented spillage phenomenon in a constant effective wedge angle class of inlets is discussed.
Document ID
19920066117
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Holland, Scott D.
(North Carolina State University, Raleigh; NASA, Langley Research Center Hampton, VA, United States)
Perkins, John N.
(North Carolina State University Raleigh, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-3099
Accession Number
92A48741
Funding Number(s)
CONTRACT_GRANT: NCC1-153
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available