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Airflow control system for supersonic inletsIn addition to fixed and variable bleed devices provided for controlling the position of a terminal shock wave in a supersonic inlet, a plurality of free piston valves are disposed around the periphery of a cowling of a supersonic engine inlet. The free piston valves are disposed in dump passageways, each of which begin at a bleed port in the cowling that is located in the throat region of the inlet, where the diameter of the centerbody is near maximum, and terminates at an opening in the cowling adjacent a free piston valve. Each valve is controlled by reference pressure.
Document ID
19740012533
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Mitchell, G. A. (NASA Lewis Research Center Cleveland, OH, United States)
Sanders, B. W. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
March 26, 1974
Subject Category
Aircraft
Report/Patent Number
Patent Number: US-PATENT-3,799,475
Patent Number: NASA-CASE-LEW-11188-1
Patent Application Number: US-PATENT-APPL-SN-152328
Accession Number
74N20646
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-3,799,475|NASA-CASE-LEW-11188-1
Patent Application
US-PATENT-APPL-SN-152328

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