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A Survey of Challenges in Aerodynamic Exhaust Nozzle Technology for Aerospace Propulsion ApplicationsThe current paper discusses aerodynamic exhaust nozzle technology challenges for aircraft and space propulsion systems. Technology advances in computational and experimental methods have led to more accurate design and analysis tools, but many major challenges continue to exist in nozzle performance, jet noise and weight reduction. New generations of aircraft and space vehicle concepts dictate that exhaust nozzles have optimum performance, low weight and acceptable noise signatures. Numerous innovative nozzle concepts have been proposed for advanced subsonic, supersonic and hypersonic vehicle configurations such as ejector, mixer-ejector, plug, single expansion ramp, altitude compensating, lobed and chevron nozzles. This paper will discuss the technology barriers that exist for exhaust nozzles as well as current research efforts in place to address the barriers.
Document ID
20020092086
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Shyne, Rickey J. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
November 1, 2002
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-2002-211977
E-13646
NAS 1.15:211977
Report Number: NASA/TM-2002-211977
Report Number: E-13646
Report Number: NAS 1.15:211977
Meeting Information
Meeting: 2002 National Conference and Technical Career Opportunity Fair
Location: Las Vegas, NV
Country: United States
Start Date: September 24, 2002
End Date: September 27, 2002
Funding Number(s)
PROJECT: RTOP 708-90-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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