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Numerical simulation of a ramjet inlet flowfield in response to large amplitude combustor pressure oscillationThe unsteady flow of a two-dimensional ramjet inlet is studied numerically by solving the Navier-Stokes equation with a two-equation turbulence model. Unsteadiness is introduced by prescribing the pressure disturbance at the inlet exit plane. The case with a sinusoidal exit plane pressure fluctuation of 20 percent of the steady exit pressure is considered. The resulting flow field exhibits a complicated interaction between the terminal shock, separation pockets and core flow. The exit plane properties feature a non-linear response to the imposed sinusoidal pressure variation.
Document ID
19840052875
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hsieh, T.
(NASA Ames Research Center Moffett Field, CA, United States)
Wardlaw, A. B., Jr.
(U.S. Navy, Naval Surface Weapons Center Silver Spring, MD, United States)
Coakley, T.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 84-1363
Accession Number
84A35662
Distribution Limits
Public
Copyright
Other

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