TY - JOUR

T1 - Numerical simulation of supersonic jet noise

AU - Schulze, Jan

AU - Sesterhenn, Jörn

AU - Schmid, Peter

AU - Bogey, Christophe

AU - de Cacqueray, Nicolas

AU - Berland, Julien

AU - Bailly, Christophe

N1 - Generated from Scopus record by KAUST IRTS on 2022-09-13

PY - 2009/3/27

Y1 - 2009/3/27

N2 - Jets with complex shock-cell structures appear in numerous technological applications. Most supersonic jets used in aeronautics will be imperfectly expanded in flight, even those from carefully designed convergent-divergent nozzles. The adaption to the ambient pressure takes place in a sequence of oblique shocks which interact with the free shear layers and produce noise. The shock/shear-layer interaction emanates a broadband noise component. This may trigger the young shear layer at the nozzle, forming a feedback loop which results in a discrete noise component called screech. Both components are undesirable from structural and environmental (cabin noise) points of view. Screech tones are known to produce sound pressure levels of 160 dB and beyond. The focus of this research project lies in the numerical simulation of jet screech. Different numerical methods are shown with LES and DNS applications of a planar rectangular and three-dimensional jet with overset grid techniques to include complex geometries for the jet nozzle. Furthermore, a shock-capturing method is developed for high-order aeroacoustic computations. It consists in applying an adaptive second-order conservative filtering to handle discontinuities, in combination with a background selective filtering to remove grid-to-grid oscillations. The magnitude of the shock-capturing filtering is determined dynamically from the flow solutions using a procedure based on a Jameson-like shock detector. Results obtained for a shock-propagation problem are shown to validate the method, which will be now used for the simulations of supersonic jets. © 2009 Springer-Verlag Berlin Heidelberg.

AB - Jets with complex shock-cell structures appear in numerous technological applications. Most supersonic jets used in aeronautics will be imperfectly expanded in flight, even those from carefully designed convergent-divergent nozzles. The adaption to the ambient pressure takes place in a sequence of oblique shocks which interact with the free shear layers and produce noise. The shock/shear-layer interaction emanates a broadband noise component. This may trigger the young shear layer at the nozzle, forming a feedback loop which results in a discrete noise component called screech. Both components are undesirable from structural and environmental (cabin noise) points of view. Screech tones are known to produce sound pressure levels of 160 dB and beyond. The focus of this research project lies in the numerical simulation of jet screech. Different numerical methods are shown with LES and DNS applications of a planar rectangular and three-dimensional jet with overset grid techniques to include complex geometries for the jet nozzle. Furthermore, a shock-capturing method is developed for high-order aeroacoustic computations. It consists in applying an adaptive second-order conservative filtering to handle discontinuities, in combination with a background selective filtering to remove grid-to-grid oscillations. The magnitude of the shock-capturing filtering is determined dynamically from the flow solutions using a procedure based on a Jameson-like shock detector. Results obtained for a shock-propagation problem are shown to validate the method, which will be now used for the simulations of supersonic jets. © 2009 Springer-Verlag Berlin Heidelberg.

UR - http://link.springer.com/10.1007/978-3-540-89956-3_2

UR - http://www.scopus.com/inward/record.url?scp=62849117737&partnerID=8YFLogxK

U2 - 10.1007/978-3-540-89956-3_2

DO - 10.1007/978-3-540-89956-3_2

M3 - Article

VL - 104

SP - 29

EP - 46

JO - Notes on Numerical Fluid Mechanics and Multidisciplinary Design

JF - Notes on Numerical Fluid Mechanics and Multidisciplinary Design

SN - 1612-2909

ER -