TY - GEN
T1 - Resolvent analysis of a biconical tactical jet nozzle
AU - Murthy, Sandeep R.
AU - Bodony, Daniel J.
N1 - This work was sponsored by the Office of Naval Research (ONR), under grant number N00014-19-1-2431. Dr. Steve Martens is the program officer. The simulations were supported by the NSF XSEDE program using allocation CTS20006 and performed on the TACC Frontera computer.
PY - 2022
Y1 - 2022
N2 - The intense noise radiated by supersonic hot jets leads to sound-induced structural vibration, fatigue and personnel-related operational difficulties. Experimental, theoretical, and computational investigations into the physics and control of jet noise have identified several important sound sources, including wavepackets, screech, Mach wave radiation, and broadband shock associated noise. Reducing the loudest sources of jet noise, without sacrificing propulsive performance, has relied on intuition, parametric survey, or optimal control techniques. With the aim of developing a more general and robust method of jet noise reduction, we present a physics-based approach, built upon a linear resolvent analysis, and apply it to reduce the noise generated by a biconical tactical jet nozzle. Our approach identifies optimal forcing/response modes of the compressible Navier-Stokes operator, linearized about a jet mean flow, that best disrupt the coherent structures that are primarily responsible for the production of jet noise. The operating conditions of the jet and nozzle geometry are motivated by tactical Naval aircraft.
AB - The intense noise radiated by supersonic hot jets leads to sound-induced structural vibration, fatigue and personnel-related operational difficulties. Experimental, theoretical, and computational investigations into the physics and control of jet noise have identified several important sound sources, including wavepackets, screech, Mach wave radiation, and broadband shock associated noise. Reducing the loudest sources of jet noise, without sacrificing propulsive performance, has relied on intuition, parametric survey, or optimal control techniques. With the aim of developing a more general and robust method of jet noise reduction, we present a physics-based approach, built upon a linear resolvent analysis, and apply it to reduce the noise generated by a biconical tactical jet nozzle. Our approach identifies optimal forcing/response modes of the compressible Navier-Stokes operator, linearized about a jet mean flow, that best disrupt the coherent structures that are primarily responsible for the production of jet noise. The operating conditions of the jet and nozzle geometry are motivated by tactical Naval aircraft.
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U2 - 10.2514/6.2022-2969
DO - 10.2514/6.2022-2969
M3 - Conference contribution
AN - SCOPUS:85135074776
SN - 9781624106644
T3 - 28th AIAA/CEAS Aeroacoustics Conference, 2022
BT - 28th AIAA/CEAS Aeroacoustics Conference, 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 28th AIAA/CEAS Aeroacoustics Conference, 2022
Y2 - 14 June 2022 through 17 June 2022
ER -