Noise sources in a low-Reynolds-number turbulent jet at Mach 0.9

By Jonathan B. Freund. Journal of Fluid Mechanics, 2001

647 citations recorded by the source corpus.

Subfields: Aerospace Engineering, Computational Mechanics, Environmental Engineering

View Paper: https://www.semanticscholar.org/paper/95ca5a9de6a35831d59efdd7b3ae26e1a188e17c

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Citations in the corpus

Flame Dynamics and Combustion Noise: Progress and Challenges (2009, background): “There are many parallel developments in the CAA domain and the literature is quite substantial (see the following publications for sample simulations of subsonic and supersonic jet noise: Bastin (1996); Freund (2001); Zhao et al. (2001); Bogey and Bailly (2006)).”
LARGE EDDY SIMULATIONS OF ROUND FREE JETS USING EXPLICIT FILTERING WITH/WITHOUT DYNAMIC SMAGORINSKY MODEL (2006, methodology): “The profile from the LESre3 jet at ReD = 2500 compares indeed favorably with that from the DNS jet at ReD = 3600 computed by Freund (2001), while the profile from the LESsf jet at high ReD agrees fairly well with that from the experimental jet at ReD = 5 · 105 of Arakeri et al. (2003).”
Importance of the nozzle-exit boundary-layer state in subsonic turbulent jets (2018, background): “…valuable physics insights, but resolution requirements and computational costs restrict the simulations to a Reynolds number of the order of 103–104 (Freund 2001; Suponitsky, Sandham & Morfey 2010; Sandberg, Sandham & Suponitsky 2012; Bühler, Kleiser & Bogey 2014a; Bühler, Obrist & Kleiser 2014b).”
On the use of microjets to suppress turbulence in a Mach 0.9 axisymmetric jet (2003, methodology): “Another motivation for the present study was to provide a set of measurements on the turbulence and mean flow characteristics of a high subsonic Mach number jet; such data for a Mach 0.9 jet is lacking, as noted by Freund (2001).”
Experimental investigation of density fluctuations in high-speed jets and correlation with generated noise (2002, background): “If ∂(2)ρ/∂t(2)−a(2)0∇(2)ρ can be measured everywhere in the flow, that will be equivalent to measuring the sum of the dipole and quadrupole terms on the right (Freund 2001). The lack of experimental data in compressible jets is primarily due to various problems in using traditional experimental tool”
COMPUTATIONAL PREDICTION OF FLOW-GENERATED SOUND (2006, methodology): “Freund (2001) reported the first DNS of a subsonic (M = 0.9) turbulent jet, which matched the experimental conditions of Stromberg et al. (1980) and showed agreement with experiment for mean-flow development, noise directivity, and noise spectra.”
Wavepacket models for supersonic jet noise (2014, methodology): “Following Freund (2001), Š is computed indirectly by evaluating the left-hand side of (2.6) with the PSE pressure solution.”
Current Status of Jet Noise Predictions Using Large-Eddy Simulation (2008, methodology): “The second method, used by BL (and originally by Freund [15]), solves the wave equation in transformed coordinates for a Kirchhoff surface S defined as a right circular cylinder, of radius Rs, with generator along the jet axis.”
Computational aeroacoustics: progress on nonlinear problems of sound generation (2004, methodology): “If a different equation set is used in the extended domain it is necessary to ensure that accurate and stable transfer of information is achieved at the grid interface (e.g. Freund et al. [43]).”
Noise Prediction for Increasingly Complex Jets. Part I: Methods and Tests (2005, background): “The first three-dimensional simulations with sound prediction appeared in the late 1990’s, with the number of grid points mounting in the millions, and past 25 millions for Freund [1] in his Direct Numerical Simulation (DNS).”
A generalized acoustic analogy (2003, background): “Goldstein (2002) showed that it can even be chosen to only pass wavenumber components with subsonic phase velocity in the streamwise direction† which, according to conventional wisdom (see, for example, Freund 2001), should cause the unsteady base flow to be non-radiating.”
Instability waves in a subsonic round jet detected using a near-field phased microphone array (2006, methodology): “In § 3, we outline a preliminary microphone array design based on direct numerical simulation (DNS) of a subsonic round jet by Freund (2001).”
Wave Packets and Turbulent Jet Noise (2013, background): “Alternatively, Cheung & Lele (2009) used an equivalent source to evaluate the far field from linear and nonlinear PSE solutions and found a close match with DNS solutions, provided the nonlinearity inherent in their transitional, two-dimensional mixing layers was properly treated.”