NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
On Hammershock Propagation in a Supersonic Flow FieldA wind tunnel test program was conducted to acquire flow-field data during a supersonic propulsion system compressor stall and inlet unstart sequence. The propulsion system consisted of a mixed-compression, two-dimensional bifurcated inlet coupled to a General Electric J85-13 turbojet engine. The propulsion system was mounted beneath a large flat plate that simulated an underwing propulsion pod installation. Transient flow-field pitot pressure and wing simulator surface static pressure data were acquired during multiple compressor stall and inlet unstart events at a free-stream Mach number of 2.20. The experimental results obtained in this investigation indicate that a supersonic propulsion system compressor stall-inlet unstart transient event adversely affects the surrounding local flow field. The data show that the stall-unstart event affects the surrounding flow field on a millisecond time scale and causes a three-dimensional expanding wave front called a hammershock to propagate outward from the inlet. The flow nearest the wing simulator separates from the surface during the transient event. At the end of the transient event, a distinct process occurs wherein the affected flow field recovers to free-stream conditions and the wing simulator boundary layer reattaches to the flow surface.
Document ID
20020081335
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Porro, A. Robert (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
July 1, 2002
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:211717
E-13469
NASA/TM-2002-211717
Meeting Information
Meeting: 23rd Congress of the International Council of the Aeronautical Sciences
Location: Toronto
Country: Canada
Start Date: September 8, 2002
End Date: September 13, 2002
Sponsors: Canadian Aeronautics and Space Inst., International Council of the Aeronautical Sciences
Funding Number(s)
PROJECT: RTOP 708-90-43
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