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Wedge Shock and Nozzle Exhaust Plume Interaction in a Supersonic Jet FlowFundamental research for sonic boom reduction is needed to quantify the interaction of shock waves generated from the aircraft wing or tail surfaces with the nozzle exhaust plume. Aft body shock waves that interact with the exhaust plume contribute to the near-field pressure signature of a vehicle. The plume and shock interaction was studied using computational fluid dynamics and compared with experimental data from a coaxial convergent-divergent nozzle flow in an open jet facility. A simple diamond-shaped wedge was used to generate the shock in the outer flow to study its impact on the inner jet flow. Results show that the compression from the wedge deflects the nozzle plume and shocks form on the opposite plume boundary. The sonic boom pressure signature of the nozzle exhaust plume was modified by the presence of the wedge. Both the experimental results and computational predictions show changes in plume deflection.
Document ID
Document Type
Conference Paper
Castner, Raymond
(NASA Glenn Research Center Cleveland, OH, United States)
Zaman, Khairul
(NASA Glenn Research Center Cleveland, OH, United States)
Fagan, Amy
(NASA Glenn Research Center Cleveland, OH, United States)
Heath, Christopher
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
April 27, 2015
Publication Date
January 13, 2014
Subject Category
Report/Patent Number
Meeting Information
AIAA SciTech 2014(National Harbor, MD)
Funding Number(s)
WBS: WBS 475122.
Distribution Limits
Work of the US Gov. Public Use Permitted.
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