NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Terminal-shock and restart control of a Mach 2.5, mixed compression inlet coupled to a turbofan engineResults of an experimental program conducted on a mixed-compression inlet coupled to a turbofan engine are presented. Open-loop frequency response data are presented that show the response of shock position (as measured by an average inlet static pressure) to sinusoidal airflow disturbances produced at the compressor face station. Also presented are results showing the effect of different passive terminations (a choke plate or a long duct) on the characteristics of the inlet. Transfer functions obtained by using experimental data are presented and compared to the experimental data. Closed-loop frequency response of shock position (with a proportional-plus-integral controller) is presented. In addition, transient data are presented that show the unstart-restart characteristics of the inlet.
Document ID
19740023159
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Baumbick, R. J. (NASA Lewis Research Center Cleveland, OH, United States)
Batterton, P. G. (NASA Lewis Research Center Cleveland, OH, United States)
Daniele, C. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-3104
E-7924
Accession Number
74N31272
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available