TY - GEN
T1 - Reducing jet noise from a biconical nozzle
AU - Murthy, Sandeep R.
AU - Bodony, Daniel J.
N1 - Publisher Copyright:
© 2024, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2024
Y1 - 2024
N2 - The intense noise radiated by jet aircraft exhaust nozzles causes structural vibration, fatigue, carrier deck personnel operational difficulties, and community environmental concerns. Prior work 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, to name a few. Reducing the loudest sources of jet noise, without sacrificing propulsive performance, has thus-far relied on intuition, parametric survey, or optimal control techniques. With the aim of developing a more general and robust method of jet noise reduction (JNR), we seek a physics-based JNR approach that is built upon a linear resolvent analysis appropriate for mean flows with strong shocks. The effect of flow discontinuities on linear analysis, including the optimal forcing and response modes that arise from resolvents, is investigated.
AB - The intense noise radiated by jet aircraft exhaust nozzles causes structural vibration, fatigue, carrier deck personnel operational difficulties, and community environmental concerns. Prior work 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, to name a few. Reducing the loudest sources of jet noise, without sacrificing propulsive performance, has thus-far relied on intuition, parametric survey, or optimal control techniques. With the aim of developing a more general and robust method of jet noise reduction (JNR), we seek a physics-based JNR approach that is built upon a linear resolvent analysis appropriate for mean flows with strong shocks. The effect of flow discontinuities on linear analysis, including the optimal forcing and response modes that arise from resolvents, is investigated.
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U2 - 10.2514/6.2024-3306
DO - 10.2514/6.2024-3306
M3 - Conference contribution
AN - SCOPUS:85202864949
SN - 9781624107207
T3 - 30th AIAA/CEAS Aeroacoustics Conference, 2024
BT - 30th AIAA/CEAS Aeroacoustics Conference, 2024
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 30th AIAA/CEAS Aeroacoustics Conference, 2024
Y2 - 4 June 2023 through 7 June 2023
ER -