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A throat-bypass stability system for a YF-12 aircraft research inlet using self-acting mechanical valvesResults of a wind tunnel investigation are presented. The inlet was modified so that airflow can be removed through a porous cowl-bleed region in the vicinity of the throat. Bleed plenum exit flow area is controlled by relief type mechanical valves. Unlike valves in previous systems, these are made for use in a high Mach flight environment and include refinements so that the system could be tested on a NASA YF-12 aircraft. The valves were designed to provide their own reference pressure; hence, do not respond to slowly varying disturbances. However, the results show that the system can absorb internal-airflow-transients that are too fast for a conventional bypass door control system and that the two systems complement each other quite well. Increased tolerance to angle of attack and Mach number changes is indicated. The valves should provide sufficient time for the inlet control system to make geometry changes required to keep the inlet started.
Document ID
19750061540
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cole, G. L.
Dustin, M. O.
Neiner, G. H.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 8, 2013
Publication Date
September 1, 1975
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 75-1181
Accession Number
75A45612
Distribution Limits
Public
Copyright
Other

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