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Accession Number N20130010181
Title Exhaust Nozzle Plume and Shock Wave Interaction.
Publication Date Feb 2013
Media Count 28p
Personal Author A. Elmiligui R. S. Castner S. Cliff
Abstract Fundamental research for sonic boom reduction is needed to quantify the interaction of shock waves generated from the aircraft wing or tail surfaces with the exhaust plume. Both the nozzle exhaust plume shape and the tail shock shape may be affected by an interaction that may alter the vehicle sonic boom signature. The plume and shock interaction was studied using Computational Fluid Dynamics simulation on two types of convergent-divergent nozzles and a simple wedge shock generator. The nozzle plume effects on the lower wedge compression region are evaluated for two- and three-dimensional nozzle plumes. Results show that the compression from the wedge deflects the nozzle plume and shocks form on the deflected lower plume boundary. The sonic boom pressure signature of the wedge is modified by the presence of the plume, and the computational predictions show significant (8 to 15 percent) changes in shock amplitude.
Keywords Boundaries
Computational fluid dynamics
Convergent-divergent nozzles
Deflection
Exhaust gases
Exhaust nozzles
Plumes
Shock wave interaction
Sonic booms
Tail surfaces


 
Source Agency National Aeronautics and Space Administration
NTIS Subject Category 51A - Aerodynamics
Corporate Author National Aeronautics and Space Administration, Cleveland, OH. NASA John H. Glenn Research Center at Lewis Field.
Document Type Technical report
Title Note N/A
NTIS Issue Number 1320
Contract Number N/A

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