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      Flow and Acoustic Fields of Rocket Jets Impinging on a Perforated Plate

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          Abstract

          The flow and acoustic fields of jets at a Mach number of 3.1 impinging on a plate at 15 D of the jet nozzle exit, where D is the nozzle diameter, have been investigated using highly resolved large-eddy simulations. The plate is perforated with a hole of diameter h = 1.33 D , 2 D , 3 D , or 4 D . The full-plate and free-jet cases have also been considered. The pressure levels are highest for the non-perforated plate and decrease as the hole diameter increases. Compared with the free jet, they are higher by about 5 dB for the full plate, 4 dB for h = 1.33 D and 2 D , 3 dB for h = 3 D , and 2 dB for h = 4 D . In the upstream direction, the broadband shock-associated noise is prevailing for the free jet. For the impinging jets, the main noise component in that direction is produced by the impingement of the jet turbulent structures on the plate. In the downstream direction, for the free jet and down to the plate for the impinging jets, the sound field is dominated by Mach waves. Downstream of the perforated plates, waves are generated by interactions between the jet flow and the plate.

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          Most cited references53

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            Numerical Treatment of Polar Coordinate Singularities

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              RADIATION AND OUTFLOW BOUNDARY CONDITIONS FOR DIRECT COMPUTATION OF ACOUSTIC AND FLOW DISTURBANCES IN A NONUNIFORM MEAN FLOW

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                Author and article information

                Contributors
                Conference
                aiaaj
                AIAA Journal
                AIAA Journal
                American Institute of Aeronautics and Astronautics
                1533-385X
                06 April 2022
                August 2022
                : 60
                : 8
                : 4614-4627
                Affiliations
                Laboratoire de Mécanique des Fluides et d'Acoustique , LMFA UMR 5509, 69130 Ecully, France
                Author notes
                [*]

                Postdoctoral Fellow; mathieu.vare@ 123456ec-lyon.fr .

                [†]

                CNRS Research Scientist; christophe.bogey@ 123456ec-lyon.fr . Associate Fellow AIAA.

                Author information
                https://orcid.org/0000-0002-8315-7470
                https://orcid.org/0000-0003-3243-747X
                Article
                J061253 J061253
                10.2514/1.J061253
                eaf5f798-e8ca-42c4-a765-aa90001d7d72
                Copyright © 2022 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
                History
                : 03 September 2021
                : 22 February 2022
                : 22 February 2022
                Page count
                Figures: 20, Tables: 2
                Funding
                Funded by: ArianeGroup
                Funded by: Direction Générale de l’Armement
                Categories
                Regular Articles
                p2263, Fluid Dynamics
                p1972, Shock Waves
                p1804, Aerodynamics
                p3282, Computational Fluid Dynamics
                p1976, Flow Regimes
                p1975, Boundary Layers
                p1973, Vortex Dynamics
                p1805, Aeroacoustics
                p3749, Turbulence
                p3278, Fluid Flow Properties

                Engineering,Physics,Mechanical engineering,Space Physics
                Supersonic Wave,Mach Numbers,Large Eddy Simulation,Jet Flow,Nozzle Walls,Boundary Layer Transition,Strouhal Numbers,Overall Sound Pressure Level,Feedback Loop,Rockets

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