Author: Clarence W. MatthewsPublisher:
ISBN:
Category : High-speed aeronautics
Languages : en
Pages : 60
Book Description
This paper presents an analysis of the ability of a perforated wall in an internal-compression supersonic inlet to control the motion of the shock due to a variety of transients in the flow values at the engine face. The method of one-dimensional unsteady-flow characteristics was used to calculate the shock motion. The perforated walls were found to contain the shock within the inlet for appreciably larger transient magnitudes than was possible with solid walls.
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Author: 
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Author: United States. Superintendent of Documents
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Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Author: