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The NASA Ames Hypersonic Combustor-Model Inlet CFD Simulations and Experimental ComparisonsComputations have been performed on a three-dimensional inlet associated with the NASA Ames combustor model for the hypersonic propulsion experiment in the 16-inch shock tunnel. The 3-dimensional inlet was designed to have the combustor inlet flow nearly two-dimensional and of sufficient mass flow necessary for combustion. The 16-inch shock tunnel experiment is a short duration test with test time of the order of milliseconds. The flow through the inlet is in chemical non-equilibrium. Two test entries have been completed and limited experimental results for the inlet region of the combustor-model are available. A number of CFD simulations, with various levels of simplifications such as 2-D simulations, 3-D simulations with and without chemical reactions, simulations with and without turbulent conditions, etc., have been performed. These simulations have helped determine the model inlet flow characteristics and the important factors that affect the combustor inlet flow and the sensitivity of the flow field to these simplifications. In the proposed paper, CFD modeling of the hypersonic inlet, results from the simulations and comparison with available experimental results will be presented.
Document ID
Document Type
Conference Paper
Venkatapathy, E.
(NASA Ames Research Center Moffett Field, CA United States)
Tokarcik-Polsky, S.
(NASA Ames Research Center Moffett Field, CA United States)
Deiwert, G. S.
(NASA Ames Research Center Moffett Field, CA United States)
Edwards, Thomas A.
Date Acquired
August 20, 2013
Publication Date
January 1, 1995
Subject Category
Fluid Mechanics And Thermodynamics
Meeting Information
Meeting: 6th International AIAA Aerospace Plane and Hypersonic Technologies Conference
Location: Chatanooga, TN
Country: United States
Start Date: April 10, 1995
End Date: April 14, 1995
Funding Number(s)
PROJECT: RTOP 505-70-62
Distribution Limits
Work of the US Gov. Public Use Permitted.

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