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Relevant bibliographies by topics / Axisymmetric subsonic flow structure

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Academic literature on the topic 'Axisymmetric subsonic flow structure'

Author: Grafiati

Published: 30 May 2022

Last updated: 31 May 2022

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Journal articles on the topic "Axisymmetric subsonic flow structure"

1

Hatta, N., R. Ishii, and H. Fujimoto. "Numerical Analysis of Gas-Particle Two-Phase Subsonic Freejets." Journal of Fluids Engineering 114, no. 3 (1992): 420–29. http://dx.doi.org/10.1115/1.2910048.

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This paper describes a numerical analysis of gas-droplet two-phase subsonic free jets in the axisymmetric system. Thermal coupling through heat transfer to droplets, as well as momentum coupling through aerodynamic drag responsible for droplet motion, is taken into account in the present numerical model. The Navier-Stokes equations for a gas-phase interacting with particle phase are solved by a time-dependent difference technique and the particle-phase is solved by a discrete particle cloud model. The jet flow structures of mixture composed of air and water-droplets with 1 μm, 5 μm, and 30 μm,

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2

Li, Songqi, and Lawrence S. Ukeiley. "Experimental investigation of the fluctuating static pressure in a subsonic axisymmetric jet." International Journal of Aeroacoustics 20, no. 3-4 (2021): 196–220. http://dx.doi.org/10.1177/1475472x211004854.

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Measuring the fluctuating static pressure within a jet has the potential to depict in-flow sources of the jet noise. In this work, the fluctuating static pressure of a subsonic axisymmetric jet was experimentally investigated using a 1/8” microphone with an aerodynamically shaped nose cone. The power spectra of the fluctuating pressure are found to follow the -7/3 scaling law at the jet centerline with the decay rate varying as the probe approaches the acoustic near field. Profiles of skewness and kurtosis reveal strong intermittency inside the jet shear layer. By applying a continuous wavelet

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3

Saxer-Felici, H. M., A. P. Saxer, A. Inderbitzin, and G. Gyarmathy. "Prediction and Measurement of Rotating Stall Cells in an Axial Compressor." Journal of Turbomachinery 121, no. 2 (1999): 365–75. http://dx.doi.org/10.1115/1.2841323.

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This paper presents a parallel numerical and experimental study of rotating stall cells in an axial compressor. Based on previous theoretical and experimental studies stressing the importance of fluid inertia and momentum exchange mechanisms in rotating stall, a numerical simulation using the Euler equations is conducted. Unsteady two-dimensional solutions of rotating stall behavior are obtained in a one-stage low subsonic axial compressor. The structure and speed of propagation of one fully developed rotating stall cell together with its associated unsteady static pressure and throughflow fie

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4

Afsar, Mohammed Z., Adrian Sescu, and Stewart J. Leib. "Modelling and prediction of the peak-radiated sound in subsonic axisymmetric air jets using acoustic analogy-based asymptotic analysis." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 377, no. 2159 (2019): 20190073. http://dx.doi.org/10.1098/rsta.2019.0073.

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This paper uses asymptotic analysis within the generalized acoustic analogy formulation (Goldstein 2003 JFM 488 , 315–333. ( doi:10.1017/S0022112003004890 )) to develop a noise prediction model for the peak sound of axisymmetric round jets at subsonic acoustic Mach numbers (Ma). The analogy shows that the exact formula for the acoustic pressure is given by a convolution product of a propagator tensor (determined by the vector Green's function of the adjoint linearized Euler equations for a given jet mean flow) and a generalized source term representing the jet turbulence field. Using a low-fre

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5

Pokora, C. D., and J. J. McGuirk. "Stereo-PIV measurements of spatio-temporal turbulence correlations in an axisymmetric jet." Journal of Fluid Mechanics 778 (July 30, 2015): 216–52. http://dx.doi.org/10.1017/jfm.2015.362.

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Stereoscopic three-component particle image velocimetry (3C-PIV) measurements have been made in a turbulent round jet to investigate the spatio-temporal correlations that are the origin of aerodynamic noise. Restricting attention to subsonic, isothermal jets, measurements were taken in a water flow experiment where, for the same Reynolds number and nozzle size, the shortest time scale of the dynamically important turbulent structures is more than an order of magnitude greater that in equivalent airflow experiments, greatly facilitating time-resolved PIV measurements. Results obtained (for a je

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6

Schmidt, Oliver T., Aaron Towne, Georgios Rigas, Tim Colonius, and Guillaume A. Brès. "Spectral analysis of jet turbulence." Journal of Fluid Mechanics 855 (September 21, 2018): 953–82. http://dx.doi.org/10.1017/jfm.2018.675.

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Informed by large-eddy simulation (LES) data and resolvent analysis of the mean flow, we examine the structure of turbulence in jets in the subsonic, transonic and supersonic regimes. Spectral (frequency-space) proper orthogonal decomposition is used to extract energy spectra and decompose the flow into energy-ranked coherent structures. The educed structures are generally well predicted by the resolvent analysis. Over a range of low frequencies and the first few azimuthal mode numbers, these jets exhibit a low-rank response characterized by Kelvin–Helmholtz (KH) type wavepackets associated wi

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7

SIMON, FRANCK, SEBASTIEN DECK, PHILIPPE GUILLEN, PIERRE SAGAUT, and ALAIN MERLEN. "Numerical simulation of the compressible mixing layer past an axisymmetric trailing edge." Journal of Fluid Mechanics 591 (October 30, 2007): 215–53. http://dx.doi.org/10.1017/s0022112007008129.

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Numerical simulation of a compressible mixing layer past an axisymmetric trailing edge is carried out for a Reynolds number based on the diameter of the trailing edge approximately equal to 2.9 × 106. The free-stream Mach number at separation is equal to 2.46, which corresponds to experiments and leads to high levels of compressibility. The present work focuses on the evolution of the turbulence field through extra strain rates and on the unsteady features of the annular shear layer. Both time-averaged and instantaneous data are used to obtain further insight into the dynamics of the flow. An

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8

Baqui, Yamin B., Anurag Agarwal, André V. G. Cavalieri, and Samuel Sinayoko. "A coherence-matched linear source mechanism for subsonic jet noise." Journal of Fluid Mechanics 776 (July 6, 2015): 235–67. http://dx.doi.org/10.1017/jfm.2015.322.

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We investigate source mechanisms for subsonic jet noise using experimentally obtained datasets of high-Reynolds-number Mach 0.4 and 0.6 turbulent jets. The focus is on the axisymmetric mode which dominates downstream sound radiation for low polar angles and the frequency range at which peak noise occurs. A linearized Euler equation (LEE) solver with an inflow boundary condition is used to generate single-frequency hydrodynamic instability waves, and the resulting near-field fluctuations and far-field acoustics are compared with those from experiments and linear parabolized stability equation (

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9

Chen, Li-Wei, Guo-Lei Wang, and Xi-Yun Lu. "Numerical investigation of a jet from a blunt body opposing a supersonic flow." Journal of Fluid Mechanics 684 (August 30, 2011): 85–110. http://dx.doi.org/10.1017/jfm.2011.276.

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AbstractNumerical investigation of a sonic jet from a blunt body opposing a supersonic flow with a free stream Mach number ${M}_{\infty } = 2. 5$ was carried out using large-eddy simulation for two total pressure ratios of the jet to the free stream, i.e. $\mathscr{P}= 0. 816$ and 1.633. Results have been validated carefully against experimental data. Various fundamental mechanisms dictating the flow phenomena, including shock/jet interaction, shock/shear-layer interaction, turbulent shear-layer evolution and coherent structures, have been studied systematically. Based on the analysis of the f

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10

Bogey, Christophe. "On noise generation in low Reynolds number temporal round jets at a Mach number of 0.9." Journal of Fluid Mechanics 859 (November 27, 2018): 1022–56. http://dx.doi.org/10.1017/jfm.2018.864.

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Two temporally developing isothermal round jets at a Mach number of 0.9 and Reynolds numbers of 3125 and 12 500 are simulated in order to investigate noise generation in high-subsonic jet flows. Snapshots and statistical properties of the flow and sound fields, including mean, root-mean-square and skewness values, spectra and auto- and cross-correlations of velocity and pressure, are presented. The jet at a Reynolds number of 12 500 develops more rapidly, exhibits more fine turbulent scales and generates more high-frequency acoustic waves than the other. In both cases, however, when the jet po

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