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Computational analysis of ramjet engine inlet interactionA computational analysis of a ramjet engine at Mach 3.5 has been conducted and compared to results obtained experimentally. This study focuses on the behavior of the inlet both with and without combustor backpressure. Increased backpressure results in separation of the body side boundary layer and a resultant static pressure rise in the inlet throat region. The computational results compare well with the experimental data for static pressure distribution through the engine, inlet throat flow profiles, and mass capture. The computational analysis slightly underpredicts the thickness of the engine body surface boundary layer and the extent of the interaction caused by backpressure; however, the interaction is observed at approximately the same level of backpressure both experimentally and computationally. This study demonstrates the ability of two different Navier-Stokes codes, namely RPLUS and PARC, to calculate the flow features of this ramjet engine and to provide more detailed information on the process of inlet interaction and unstart.
Document ID
19920066120
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Duncan, Beverly
(Sverdrup Technology, Inc. Brook Park, OH, United States)
Thomas, Scott
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-3102
Accession Number
92A48744
Distribution Limits
Public
Copyright
Other

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