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Journal articles on the topic 'Axisymmetric subsonic flow structure'

Author: Grafiati

Published: 30 May 2022

Last updated: 31 May 2022

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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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11

TINNEY, C. E., M. N. GLAUSER, and L. S. UKEILEY. "Low-dimensional characteristics of a transonic jet. Part 1. Proper orthogonal decomposition." Journal of Fluid Mechanics 612 (October 10, 2008): 107–41. http://dx.doi.org/10.1017/s0022112008002978.

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An experimental investigation concerning the most energetic turbulent features of the flow exiting from an axisymmetric converging nozzle at Mach 0.85 and ambient temperature is discussed using planar optical measurement techniques. The arrangement of the particle image velocimetry (PIV) system allows for all three components of the velocity field to be captured along the (r, θ)-plane of the jet at discrete streamwise locations between x/D=3.0 and 8.0 in 0.25 diameter increments. The ensemble-averaged (time-suppressed) two-point full Reynolds stress matrix is constructed from which the integra

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12

Vasin, A. D. "Thin axisymmetric cavities in a subsonic compressible flow." Fluid Dynamics 22, no. 5 (1988): 808–11. http://dx.doi.org/10.1007/bf01051708.

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13

Baskaran, Kabilan, and K. Srinivasan. "Aeroacoustic characteristics of subsonic flow from axisymmetric pipe-cavities." Physics of Fluids 31, no. 10 (2019): 106107. http://dx.doi.org/10.1063/1.5123661.

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14

Broze, George, and Fazle Hussain. "Nonlinear dynamics of forced transitional jets: periodic and chaotic attractors." Journal of Fluid Mechanics 263 (March 25, 1994): 93–132. http://dx.doi.org/10.1017/s0022112094004040.

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Conclusive experimental evidence is presented for the existence of a low-dimensional temporal dynamical system in an open flow, namely the near field of an axisymmetric, subsonic free jet. An initially laminar jet (4 cm air jet in the Reynolds number range 1.1 × 104 [Lt ] ReD × 9.1 × 104) with a top-hat profile was studied using single-frequency, longitudinal, bulk excitation. Two non-dimensional control parameters – forcing frequency StD (≡fexD/Ue, where fez is the excitation frequency, D is the jet exit diameter and Ue is the exit velocity) and forcing amplitude af (≡ u’f/Ue, where u’f is th

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15

Busse, C. A., and R. I. Loehrke. "Subsonic Pressure Recovery in Cylindrical Condensers." Journal of Heat Transfer 111, no. 2 (1989): 533–37. http://dx.doi.org/10.1115/1.3250710.

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A method is presented for predicting laminar, subsonic flow in axisymmetric cylindrical heat pipe condensers. The method involves the use of the boundary layer approximation and a noncontinuous power series to describe the velocity profile under conditions including strong axial flow reversal. A comparison between laminar predictions and measurements indicates that transition to turbulent flow in the condenser begins when the absolute value of the radial Reynolds number exceeds 6. The condenser pressure recovery in the turbulent regime can be calculated from the momentum flow at the condenser

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16

Porteiro, J. L. F., and V. Perez-Villar. "Wake development in turbulent subsonic axisymmetric flows." Experiments in Fluids 21, no. 3 (1996): 145–50. http://dx.doi.org/10.1007/bf00191685.

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17

Peskova, E. E. "Numerical modeling of subsonic axisymmetric reacting gas flows." Journal of Physics: Conference Series 2057, no. 1 (2021): 012071. http://dx.doi.org/10.1088/1742-6596/2057/1/012071.

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Abstract A numerical algorithm is developed and implemented for modelling axisymmetric subsonic reacting gas flows based on a previously created program for plane flows. The system of Navier-Stokes equations in the low Mach number limit is used as a mathematical model. Calculations of ethane pyrolysis for axisymmetric and plane flow of mixture at heat supply from the reactor’s walls are carried out. Through the interplay of the developed code and the code for plane flows it becomes possible to identify the geometric factor role at the presence of a large number of nonlinear physicochemical pro

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18

Samanta, Arnab. "On the axisymmetric stability of heated supersonic round jets." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 472, no. 2188 (2016): 20150817. http://dx.doi.org/10.1098/rspa.2015.0817.

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We perform an inviscid, spatial stability analysis of supersonic, heated round jets with the mean properties assumed uniform on either side of the jet shear layer, modelled here via a cylindrical vortex sheet. Apart from the hydrodynamic Kelvin–Helmholtz (K–H) wave, the spatial growth rates of the acoustically coupled supersonic and subsonic instability waves are computed for axisymmetric conditions ( m =0) to analyse their role on the jet stability, under increased heating and compressibility. With the ambient stationary, supersonic instability waves may exist for any jet Mach number M j ≥2,

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19

Tran The Hung. "AERODYNAMIC CHARACTERISTICS OF FLOW OVER BOAT-TAIL MODELS AT SUBSONIC AND SUPERSONIC CONDITIONS." Journal of Military Science and Technology, no. 75A (November 11, 2021): 60–69. http://dx.doi.org/10.54939/1859-1043.j.mst.75a.2021.60-69.

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In this study, the flow behavior and drag of the axisymmetric model at subsonic and supersonic speeds were investigated by a numerical approach. The numerical results were validated with previous experimental results to determine the model's accuracy. The numerical results showed that the optimal angles reduce from 14° at subsonic conditions to 6° ÷ 8° at supersonic conditions. At the supersonic speeds, shock waves occur at the head and boat-tail of the model, which leads to changes in the pressure distribution and drag of the model. The flow behavior and velocity distribution around the model

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20

Naser, J. A., and A. D. Gosman. "Prediction of Compressible Subsonic Flow through an Axisymmetric Exhaust Valve-port Assembly." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 209, no. 4 (1995): 289–95. http://dx.doi.org/10.1243/pime_proc_1995_209_216_02.

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Flow details through an axisymmetric exhaust valve-port assembly have been investigated numerically. Computations were performed for steady compressible subsonic air flow at different valve lifts. The numerical procedure used for this purpose solves the governing equations using the SIMPLE algorithm. The governing equations are expressed in a general curvilinear coordinate system and are discretized in a finite volume fashion. The time-averaged governing equations are closed using the k–e. turbulence model. The predictions are assessed by comparing with the available experimental flow field da

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21

Miller, P., J. Agrell, J. Olsson, and K. Sjörs. "Axisymmetric afterbody experiments for CFD validation." Aeronautical Journal 98, no. 974 (1994): 137–46. http://dx.doi.org/10.1017/s0001924000049988.

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Summary An experiment is described which was undertaken specifically to provide CFD validation data for the case of transonic flow over nozzle afterbodies. The tests were undertaken with the AGARD standard 10° and 15° axisymmetric boat-tail geometries. Onset Mach numbers in the range 0·80-0·99 and subsonic and under-expanded jet plumes were employed in the tests. Test conditions were selected which provided a range of afterbody flow features from largely attached to shock-induced separated flows. A uniquely detailed set of surface pressure and flowfield data are presented. The flow data were a

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22

Vasin, A. D. "Calculation of axisymmetric cavities downstream of a disk in subsonic compressible fluid flow." Fluid Dynamics 31, no. 2 (1996): 240–48. http://dx.doi.org/10.1007/bf02029683.

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23

Du, Yanfeng, Cong Wang, and Yan Zhou. "A study on supercavitation in axisymmetric subsonic liquid flow past slender conical body." European Journal of Mechanics - B/Fluids 72 (November 2018): 264–74. http://dx.doi.org/10.1016/j.euromechflu.2018.06.004.

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24

Benard, N., J. Jolibois, M. Forte, G. Touchard, and E. Moreau. "Control of an axisymmetric subsonic air jet by plasma actuator." Experiments in Fluids 43, no. 4 (2007): 603–16. http://dx.doi.org/10.1007/s00348-007-0344-9.

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25

Ziwan, Li, and V. L. Varsegov. "Computational Study of Interaction of Transverse Subsonic and Supersonic Axisymmetric Jets with Main Flow." Russian Aeronautics 62, no. 3 (2019): 438–47. http://dx.doi.org/10.3103/s1068799819030115.

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26

Sandberg, R. D., and B. J. Tester. "Mach-number scaling of individual azimuthal modes of subsonic co-flowing jets." Journal of Fluid Mechanics 793 (March 14, 2016): 209–28. http://dx.doi.org/10.1017/jfm.2016.133.

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The Mach-number scaling of the individual azimuthal modes of jet mixing noise was studied for jets in flight conditions, i.e. with co-flow. The data were obtained via a series of direct numerical simulations (DNS), performed of fully turbulent jets with a target Reynolds number, based on nozzle diameter, of $Re_{jet}=8000$. The DNS included a pipe 25 diameters in length in order to ensure that the flow developed to a fully turbulent state before exiting into a laminar co-flow, and to account for all possible noise generation mechanisms. To allow for a detailed study of the jet mixing noise com

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27

Guslyakova, E. V. "Instability and structure of axisymmetric rotating flow." Fluid Dynamics 28, no. 5 (1994): 638–43. http://dx.doi.org/10.1007/bf01050046.

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28

Zhang, X., X. X. Chen, and C. L. Morfey. "Acoustic Radiation from a Semi-Infinite Duct With a Subsonic Jet." International Journal of Aeroacoustics 4, no. 1-2 (2005): 169–84. http://dx.doi.org/10.1260/1475472053730075.

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The radiation of high-order spinning modes from a semi-infinite exhaust duct is studied numerically. The issues involved have applications to noise radiation from the exhaust duct of an aircraft engine. The numerical method is based on solutions of linearised Euler equations (LEE) for propagation in the duct and near field, and the acoustic analogy for far field radiation. A 2.5D formulation of a linearised Euler equation model is employed to accommodate a single spinning mode propagating over an axisymmetric mean flow field. In the solution process, acoustic waves are admitted into the propag

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29

Yan, Dongfeng, Zhijun Wei, Kan Xie, Changchao Guo, Wan Tang, and Ningfei Wang. "Study of the vortex structure of a subsonic jet in an axisymmetric transonic nozzle." Physics of Fluids 32, no. 7 (2020): 076109. http://dx.doi.org/10.1063/5.0008796.

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30

Hu, Shuzhen, Xingen Lu, Hongwu Zhang, Junqiang Zhu, and Qiang Xu. "Numerical investigation of a high-subsonic axial-flow compressor rotor with non-axisymmetric hub endwall." Journal of Thermal Science 19, no. 1 (2010): 14–20. http://dx.doi.org/10.1007/s11630-010-0014-8.

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31

Jelínek, Tomáš, Erik Flídr, Martin Němec, and Jan Šimák. "Test Facility for High-Speed Probe Calibration." EPJ Web of Conferences 213 (2019): 02033. http://dx.doi.org/10.1051/epjconf/201921302033.

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A new test facility was built up as a part of a closed-loop transonic wind tunnel in VZLU´s High-speed Aerodynamics Department. The wind tunnel is driven by a twelve stage radial compressor and Mach and Reynolds numbers can be changed by the compressor speed and by the total pressure in the wind tunnel loop by a set of vacuum pumps, respectively. The facility consists of an axisymmetric subsonic nozzle with an exit diameter de = 100 mm. The subsonic nozzle is designed for regimes up to M = 1 at the nozzle outlet. At the nozzle inlet there is a set of a honeycomb and screens to ensure the flow

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32

Legras, Guillaume, Isabelle Trébinjac, Nicolas Gourdain, Xavier Ottavy, and Lionel Castillon. "A Novel Approach to Evaluate the Benefits of Casing Treatment in Axial Compressors." International Journal of Rotating Machinery 2012 (2012): 1–19. http://dx.doi.org/10.1155/2012/975407.

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Passive control devices based on casing treatments have already shown their capability to improve the flow stability in axial compressors. However, their optimization remains complex due to a partial understanding of the related physical mechanisms. In order to quantitatively assess the interaction between slots and the blade tip flow, the present paper develops a novel analysis methodology based on a control-volume approach located in the rotor tip region. This methodology may be used for analyzing the casing treatment based on both axi- and non-axisymmetric slots design. The second issue of

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33

MIYATA, Masafumi. "Axisymmetric Annular Jet : Flow Structure Near Nozzle Exit." Proceedings of the JSME annual meeting 2003.2 (2003): 151–52. http://dx.doi.org/10.1299/jsmemecjo.2003.2.0_151.

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34

Lyubimov, Dmitriy, and Alena Fedorenko. "External flow velocity and synthetic jets parameters influence on cavity flow structure and acoustics characteristics using RANS/ILES." International Journal of Aeroacoustics 17, no. 3 (2018): 259–74. http://dx.doi.org/10.1177/1475472x18763858.

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An influence of synthetic jets on the flow in a three-dimensional cavity M219 was studied using RANS/ILES method. Calculations were performed for Mach numbers M0 = 0.85 and M0 = 1.5. Synthetic jets’ operating parameters such as their position, number, frequency, and amplitude were varied. An impact of these parameters and M0 on flow in the cavity, distributions, and levels of pressure fluctuations on the cavity walls as well as the narrowband spectra of pressure fluctuations were obtained. Synthetic jets located in front of a cavity may reduce peak pressure pulsations on the cavity back wall b

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35

Yang, Hai-Hua, Lin Zhou, Xing-Chen Zhang, Zhen-Hua Wan, and De-Jun Sun. "Nonlinear interaction of instability waves and vortex-pairing noise in axisymmetric subsonic jets." Fluid Dynamics Research 48, no. 5 (2016): 055502. http://dx.doi.org/10.1088/0169-5983/48/5/055502.

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36

Madaliev, Murodil Erkinjon oglu, та Dilshod Primkulovich Navruzov. "RESEARCH OF RESEARCH OF νt-92 TURBULENCE MODEL FOR CALCULATING AN AXISYMMETRIC SOUND JET". Scientific Reports of Bukhara State University 4, № 2 (2020): 82–90. http://dx.doi.org/10.52297/2181-1466/2020/4/2/1.

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A comparative analysis of the use of the turbulence model is carried out: the one-parameter Secundov νt-92 model on the problem of an axisymmetric subsonic jet. The calculation results are compared with experimental results on the propagation of speed, voltage, and temperature. The flow is turbulent, therefore, as a mathematical model, the system of Navier-Stokes equations averaged by Reynolds (RANS) is used. For the posed problem, a generalized stream function ψ is introduced. A comparison was made of the results of the νt-92 model with experimental data from [5] the dimensionless axial veloc

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37

Симашов, Р. Р., and С. В. Чехранов. "Determination of mass flow characteristics of supersonic axisymmetric nozzle diaphragms in modeling variable duties of low-consumption turbines." MORSKIE INTELLEKTUAL`NYE TEHNOLOGII), no. 4(50) (December 17, 2020): 39–43. http://dx.doi.org/10.37220/mit.2020.50.4.070.

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В работе приводятся обобщающие зависимости коэффициентов расхода сопловых аппаратов со сверхзвуковыми осесимметричными соплами в широком диапазоне изменения определяющих геометрических и режимных параметров. Предложена двухпараметрическая функция, учитывающая влияние расположения сопел в сопловом аппарате и степени конфузорности дозвуковой части осесимметричного сопла на коэффициент расхода. Показано слабое влияние на коэффициент расхода относительного радиуса закругления стенки в узкой части сопла и относительной длины дозвуковой части сопла в области их оптимальных значений определенных по м

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38

Masud, J. "Flow field and performance analysis of an integrated diverterless supersonic inlet." Aeronautical Journal 115, no. 1170 (2011): 471–80. http://dx.doi.org/10.1017/s0001924000006114.

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Abstract In this paper the computed flow and performance characteristics at low angle-of-attack (AOA) of an integrated diverterless supersonic inlet (DSI) are presented. The subsonic characteristics are evaluated at M∞ = 0·8 while the supersonic characteristics are evaluated at M∞= 1·7, which is near the design Mach number for the intake. In addition to the external flow features, the internal intake duct flow behaviour is also evaluated. The results of this study indicate effective boundary layer diversion due to the ‘bump’ compression surface in both subsonic and supersonic regimes. At M∞ =

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39

Chandola, Gaurav, Xin Huang, and David Estruch-Samper. "Highly separated axisymmetric step shock-wave/turbulent-boundary-layer interaction." Journal of Fluid Mechanics 828 (September 6, 2017): 236–70. http://dx.doi.org/10.1017/jfm.2017.522.

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The unsteadiness of a shock-wave/turbulent-boundary-layer interaction induced by an axisymmetric step (cylinder/$90^{\circ }$-disk) is investigated experimentally at Mach 3.9. A large-scale separation of the order of previously reported incoming turbulent superstructures is induced ahead of the step ${\sim}30\unicode[STIX]{x1D6FF}_{o}$ and followed by a downstream separation of ${\sim}10\unicode[STIX]{x1D6FF}_{o}$ behind it, where $\unicode[STIX]{x1D6FF}_{o}$ is the incoming boundary-layer thickness. Narrowband high-frequency instabilities shift gradually to more moderate frequencies along the

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40

da Silva, A. R., G. P. Scavone, and A. Lefebvre. "Sound reflection at the open end of axisymmetric ducts issuing a subsonic mean flow: A numerical study." Journal of Sound and Vibration 327, no. 3-5 (2009): 507–28. http://dx.doi.org/10.1016/j.jsv.2009.06.027.

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41

Starikov, O. Yu. "The study of the induction of subsonic wind tunnels with an axisymmetric working part." Fluid Dynamics 20, no. 1 (1985): 130–33. http://dx.doi.org/10.1007/bf01097375.

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42

Hyhlík, Tomáš. "Method of Vortex Structure Identification in Axisymmetric Flow Field." Manufacturing Technology 15, no. 5 (2015): 842–45. http://dx.doi.org/10.21062/ujep/x.2015/a/1213-2489/mt/15/5/842.

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Singh, Rakesh K., and Ram S. Azad. "Structure of Turbulence in an Incipient-Separating Axisymmetric Flow." Journal of Fluids Engineering 117, no. 3 (1995): 433–38. http://dx.doi.org/10.1115/1.2817280.

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The relative intensity, skewness, and flatness of fluctuating streamwise velocity along the centerline of an 8 deg included angle conical diffuser show dramatic rapid growth in the final stages of the flow under the increasing influence of growing instantaneous reversals in the wall-layer. Pulsed-wire anemometry was effectively used for the measurement of quantitative instantaneous reversals and the turbulent flow field. In the severe adverse pressure gradient of the diffuser flow, the maxima of the streamwise and transverse fluctuating velocities, Reynolds shear stress, and turbulent energy p

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Damle, S. V., T. Q. Dang, and D. R. Reddy. "Throughflow Method for Turbomachines Applicable for All Flow Regimes." Journal of Turbomachinery 119, no. 2 (1997): 256–62. http://dx.doi.org/10.1115/1.2841108.

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A new axisymmetric throughflow method for analyzing and designing turbomachines is proposed. This method utilizes body-force terms to represent blade forces and viscous losses. The resulting equations of motion, which include these body-force terms, are cast in terms of conservative variables and are solved using a finite-volume time-stepping scheme. In the inverse mode, the swirl schedule in the bladed regions (i.e., the radius times the tangential velocity rVθ) is the primary specified flow quantity, and the corresponding blade shape is sought after. In the analysis mode, the blade geometry

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Jung, Seo Yoon, and Hyung Jin Sung. "Flow structure and flow-induced noise in an axisymmetric cavity with lids." Journal of Mechanical Science and Technology 30, no. 7 (2016): 3229–41. http://dx.doi.org/10.1007/s12206-016-0631-6.

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Yaman, Kemal. "Subsonic Flutter of Cantilever Rectangular PC Plate Structure." International Journal of Aerospace Engineering 2016 (2016): 1–10. http://dx.doi.org/10.1155/2016/9212364.

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Flutter characteristics of cantilever rectangular flexible plate structure under incompressible flow regime are investigated by comparing the results of commercial flutter analysis program ZAERO©with wind tunnel tests conducted in Ankara Wind Tunnel (ART). A rectangular polycarbonate (PC) plate, 5 × 125 × 1000 mm in dimension, is used for both numerical and experimental investigations. Analysis and test results are very compatible with each other. A comparison between two different solution methods (g-methodandk-method) of ZAERO©is also done. It is seen that thek-methodgives a closer result th

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Cavalieri, André V. G., Daniel Rodríguez, Peter Jordan, Tim Colonius, and Yves Gervais. "Wavepackets in the velocity field of turbulent jets." Journal of Fluid Mechanics 730 (August 2, 2013): 559–92. http://dx.doi.org/10.1017/jfm.2013.346.

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AbstractWe study the velocity fields of unforced, high Reynolds number, subsonic jets, issuing from round nozzles with turbulent boundary layers. The objective of the study is to educe wavepackets in such flows and to explore their relationship with the radiated sound. The velocity field is measured using a hot-wire anemometer and a stereoscopic, time-resolved PIV system. The field can be decomposed into frequency and azimuthal Fourier modes. The low-angle sound radiation is measured synchronously with a microphone ring array. Consistent with previous observations, the azimuthal wavenumber spe

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Miao, Junjie, and Yuxin Fan. "Influence of struts on cavity at subsonic speeds: Flow characteristics." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 14 (2019): 5369–79. http://dx.doi.org/10.1177/0954410019843726.

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Cavity–strut combined flame holder is a promising choice for turbine-based combined cycle engines with its excellent fuel distribution and flame stabilization. In this paper, the effects of the strut structure parameters on the flow characteristics in the cavity were investigated by using particle image velocimetry and numerical simulation. Experimental and numerical results show that the struts induce complex three-dimensional flow patterns, which have a significant influence on the cavity transverse vortex. The relative position between the cavity and the strut influences the critical length

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MELIGA, P., D. SIPP, and J. M. CHOMAZ. "Effect of compressibility on the global stability of axisymmetric wake flows." Journal of Fluid Mechanics 660 (August 19, 2010): 499–526. http://dx.doi.org/10.1017/s002211201000279x.

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We study the linear dynamics of global eigenmodes in compressible axisymmetric wake flows, up to the high subsonic regime. We consider both an afterbody flow at zero angle of attack and a sphere, and find that the sequence of bifurcations destabilizing the axisymmetric steady flow is independent of the Mach number and reminiscent of that documented in the incompressible wake past a sphere and a disk (Natarajan & Acrivos, J. Fluid Mech., vol. 254, 1993, p. 323), hence suggesting that the onset of unsteadiness in this class of flows results from a global instability. We determine the boundar

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Rusak, Zvi, Jung J. Choi, Nicholas Bourquard, and Shixiao Wang. "Vortex breakdown of compressible subsonic swirling flows in a finite-length straight circular pipe." Journal of Fluid Mechanics 781 (September 16, 2015): 3–27. http://dx.doi.org/10.1017/jfm.2015.482.

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A global analysis of steady states of inviscid compressible subsonic swirling flows in a finite-length straight circular pipe is developed. A nonlinear partial differential equation for the solution of the flow stream function is derived in terms of the inlet flow specific total enthalpy, specific entropy and circulation functions. The equation reflects the complicated thermo–physical interactions in the flows. Several types of solutions of the resulting nonlinear ordinary differential equation for the columnar case together with a flow force condition describe the outlet state of the flow in

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