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The Mach disc in truncated plug nozzle flowsThe first shock reflection within truncated plug nozzle propulsive jets is investigated experimentally using a free jet blow-down facility. The locations and sizes of these reflections in axisymmetric plug nozzles, with cylindrical shrouds and conical truncated plugs, are presented. Data are presented for a range of ambient to nozzle total pressure ratios. The effects of Mach disk location and size resulting from changing plug length and from varying amounts of base bleed are documented.
Document ID
19750049896
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Giel, T. V., Jr.
(ARO, Inc. Engine Test Facility, Arnold Air Force Station, Tenn., United States)
Mueller, T. J.
(Notre Dame, University Notre Dame, Ind., United States)
Date Acquired
August 8, 2013
Publication Date
June 1, 1975
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 75-886
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference
Location: Hartford, CT
Start Date: June 16, 1975
End Date: June 18, 1975
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
75A33968
Funding Number(s)
CONTRACT_GRANT: NAS8-25601
Distribution Limits
Public
Copyright
Other

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