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Exhaust Nozzle Plume Effects on Sonic Boom Test Results for Vectored NozzlesReducing or eliminating the operational restrictions of supersonic aircraft over populated areas has led to extensive research at NASA. Restrictions were due to the disturbance of the sonic boom, caused by the coalescence of shock waves formed off the aircraft. Recent work has been performed to reduce the magnitude of the sonic boom N-wave generated by airplane components with a focus on shock waves caused by the exhaust nozzle plume. Previous Computational Fluid Dynamics (CFD) analysis showed how the shock wave formed at the nozzle lip interacts with the nozzle boat-tail expansion wave. An experiment was conducted in the 1- by 1-foot Supersonic Wind Tunnel (SWT) at the NASA Glenn Research Center. Results show how the shock generated at the nozzle lip affects the near field pressure signature, and thereby the potential sonic boom contribution for a nozzle at vector angles from 3 to 8 . The experiment was based on the NASA F-15 nozzle used in the Lift and Nozzle Change Effects on Tail Shock experiment, which possessed a large external boat-tail angle. In this case, the large boat-tail angle caused a dramatic expansion, which dominated the near field pressure signature. The impact of nozzle vector angle and nozzle pressure ratio are summarized.
Document ID
20120002932
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Castner, Raymond (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 25, 2013
Publication Date
February 1, 2012
Subject Category
Aeronautics (General)
Report/Patent Number
E-17790
NASA/TM-2012-217229
AIAA Paper-2011-5974
Meeting Information
Meeting: 47th Joint Propulsion Conference and Exhibit
Location: San Diego, CA
Country: United States
Start Date: July 31, 2011
End Date: August 3, 2011
Sponsors: American Inst. of Aeronautics and Astronautics, American Society of Mechanical Engineers, American Society for Electrical Engineers, Society of Automotive Engineers, Inc.
Funding Number(s)
WBS: WBS 984754.02.07.03.13.05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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