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Study of shock-induced combustion using an implicit TVD schemeThe supersonic combustion flowfields associated with various hypersonic propulsion systems, such as the ram accelerator, the oblique detonation wave engine, and the scramjet, are being investigated using a new computational fluid dynamics (CFD) code. The code solves the fully coupled Reynolds-averaged Navier-Stokes equations and species continuity equations in an efficient manner. It employs an iterative method and a second order differencing scheme to improve computational efficiency. The code is currently being applied to study shock wave/boundary layer interactions in premixed combustible gases, and to investigate the ram accelerator concept. Results obtained for a ram accelerator configuration indicate a new combustion mechanism in which a shock wave induces combustion in the boundary layer, which then propagates outward and downstream. The combustion process creates a high pressure region over the back of the projectile resulting in a net positive thrust forward.
Document ID
19920016573
Document Type
Conference Paper
Authors
Yungster, Shayne
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1992
Publication Information
Publication: Computational Fluid Dynamics
Subject Category
Inorganic And Physical Chemistry
Accession Number
92N25816
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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