NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Computational effects of inlet representation on powered hypersonic, airbreathing modelsComputational results are presented to illustrate the powered aftbody effects of representing the scramjet inlet on a generic hypersonic vehicle with a fairing, to divert the external flow, as compared to an operating flow-through scramjet inlet. This study is pertinent to the ground testing of hypersonic, airbreathing models employing scramjet exhaust flow simulation in typical small-scale hypersonic wind tunnels. The comparison of aftbody effects due to inlet representation is well-suited for computational study, since small model size typically precludes the ability to ingest flow into the inlet and perform exhaust simulation at the same time. Two-dimensional analysis indicates that, although flowfield differences exist for the two types of inlet representations, little, if any, difference in surface aftbody characteristics is caused by fairing over the inlet.
Document ID
19930068430
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Huebner, Lawrence D.
(NASA Langley Research Center Hampton, VA, United States)
Tatum, Kenneth E.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
October 1, 1993
Publication Information
Publication: Journal of Aircraft
Volume: 30
Issue: 5
ISSN: 0021-8669
Subject Category
Aerodynamics
Accession Number
93A52427
Distribution Limits
Public
Copyright
Other

Available Downloads

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