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Journal articles on the topic 'Low Mach regime'

Author: Grafiati

Published: 12 October 2024

Last updated: 31 July 2025

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1

Faccanoni, Gloria, Bérénice Grec, and Yohan Penel. "A homogeneous relaxation low mach number model." ESAIM: Mathematical Modelling and Numerical Analysis 55, no. 4 (2021): 1569–98. http://dx.doi.org/10.1051/m2an/2021032.

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In the present paper, we investigate a new homogeneous relaxation model describing the behaviour of a two-phase fluid flow in a low Mach number regime, which can be obtained as a low Mach number approximation of the well-known HRM. For this specific model, we derive an equation of state to describe the thermodynamics of the two-phase fluid. We prove some theoretical properties satisfied by the solutions of the model, and provide a well-balanced scheme. To go further, we investigate the instantaneous relaxation regime, and prove the formal convergence of this model towards the low Mach number a

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2

Jardine, M., and E. R. Priest. "Energetics of compressible models of fast steady-state magnetic reconnection." Journal of Plasma Physics 43, no. 1 (1990): 141–50. http://dx.doi.org/10.1017/s0022377800014677.

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An understanding of the energy transfer that takes place during magnetic reconnection is crucial to the study of this fundamental process. It depends on two factors: the type of reconnection regime (which is determined by the boundary conditions) and the degree of compressibility. Here we examine the role of compressibility in the energetics of a family of reconnection models. When the inflow Mach number (or reconnection rate) Me is small the effects of compressibility may be more important than the differences between regimes. We find that for a slow-compression regime with Me = 0·005 compres

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3

Ji, Zifei, Huiqiang Zhang, and Bing Wang. "Thrust control strategy based on the minimum combustor inlet Mach number to enhance the overall performance of a scramjet engine." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 13 (2019): 4810–24. http://dx.doi.org/10.1177/0954410019830816.

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A lower combustor inlet Mach number is desirable in order to design a compact, lightweight combustor and boost the overall performance of the scramjet engine. In this study, a thrust control strategy is proposed for a hydrogen-fueled scramjet taking into account the operating limitations, which is called the minimum combustor inlet Mach number rule since the combustor inlet Mach number is used as the control variable. By scheduling the fuel supply and modifying the intake geometry, the combustor inlet Mach number can be minimized while ensuring a certain thrust output within the operation cons

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4

Baus, Franziska, Axel Klar, Nicole Marheineke, and Raimund Wegener. "Low-Mach-number and slenderness limit for elastic Cosserat rods and its numerical investigation." Asymptotic Analysis 120, no. 1-2 (2020): 103–21. http://dx.doi.org/10.3233/asy-191581.

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This paper deals with the relation of the dynamic elastic Cosserat rod model and the Kirchhoff beam equations. We show that the Kirchhoff beam without angular inertia is the asymptotic limit of the Cosserat rod, as the slenderness parameter (ratio between rod diameter and length) and the Mach number (ratio between rod velocity and typical speed of sound) approach zero, i.e., low-Mach-number–slenderness limit. The asymptotic framework is exact up to fourth order in the small parameter and reveals a mathematical structure that allows a uniform handling of the transition regime between the models

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5

Shajii, A., and J. P. Freidberg. "Theory of low Mach number compressible flow in a channel." Journal of Fluid Mechanics 313 (April 25, 1996): 131–45. http://dx.doi.org/10.1017/s0022112096002157.

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The properties of a relatively uncommon regime of fluid dynamics, low Mach number compressible flow are investigated. This regime, which is characterized by an exceptionally large channel aspect ratio L/d ∼ 106 leads to highly subsonic flows in which friction dominates inertia. Even so, because of the large aspect ratio, finite pressure, temperature, and density gradients are required, implying that compressibility effects are also important. Analytical results are presented which show, somewhat unexpectedly, that for forced channel flow, steady-state solutions exist only below a critical valu

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6

Turner, Stephen E., Lok C. Lam, Mohammad Faghri, and Otto J. Gregory. "Experimental Investigation of Gas Flow in Microchannels." Journal of Heat Transfer 126, no. 5 (2004): 753–63. http://dx.doi.org/10.1115/1.1797036.

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This paper presents an experimental investigation of laminar gas flow through microchannels. The independent variables: relative surface roughness, Knudsen number and Mach number were systematically varied to determine their influence on the friction factor. The microchannels were etched into silicon wafers, capped with glass, and have hydraulic diameters between 5 and 96 μm. The pressure was measured at seven locations along the channel length to determine local values of Knudsen number, Mach number and friction factor. All measurements were made in the laminar flow regime with Reynolds numbe

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7

Tomasini, M., N. Dolez, and J. Léorat. "Instability of a rotating shear layer in the transonic regime." Journal of Fluid Mechanics 306 (January 10, 1996): 59–82. http://dx.doi.org/10.1017/s0022112096001231.

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We have studied numerically the stability of a two-dimensional Couette flow in a polytropic fluid subjected to a localized shear, using a pseudo-spectral method (Fourier-Chebyshev). The polytropic index has been chosen equal to 2 and a radial force (pseudo-gravity) is introduced in order to perform comparisons with the shallow water experimental results. When the Reynolds number is not too low, the initial flow which is purely azimuthal becomes unstable and a stable rotating pattern is formed, with a number of azimuthal modes which decreases when the Mach number increases. A qualitative agreem

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8

Pröbsting, S., Y. Yang, H. Zhang, P. Li, Y. Liu, and Y. Li. "Effect of Mach number on the aeroacoustic feedback loop generating airfoil tonal noise." Physics of Fluids 34, no. 9 (2022): 094115. http://dx.doi.org/10.1063/5.0107181.

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Airfoil tonal noise emission at low-to-moderate Reynolds number and flow conditions featuring a laminar separation bubble close to the trailing edge is often related to an aeroacoustic feedback mechanism and, therefore, the Mach number is a primary parameter for the flow field and noise generation. This study experimentally explores the effect of the Mach number on airfoil tonal noise generation in the nominally incompressible flow regime. Using airfoil profiles of different chord lengths, the Mach number is varied for a constant Reynolds number. Acoustic and flow field measurements for a rang

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9

Beccantini, A., E. Studer, S. Gounand, et al. "Numerical simulations of a transient injection flow at low Mach number regime." International Journal for Numerical Methods in Engineering 76, no. 5 (2008): 662–96. http://dx.doi.org/10.1002/nme.2331.

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10

Dubrovin, Kirill, Lev Yarkov, Alexandr Zarvin, et al. "Numerical and Experimental Simulation of Supersonic Gas Outflow into a Low-Density Medium." Aerospace 11, no. 11 (2024): 905. http://dx.doi.org/10.3390/aerospace11110905.

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This study is aimed at developing methods for the experimental and numerical simulation of the outflow of underexpanded gas jets into a rarefied medium. The numerical method is based on using Navier–Stokes equations in the continuum flow regime and the direct simulation Monte Carlo method in the transitional flow regime. The experimental method includes the modeling of jet flows in the LEMPUS-2 gas-dynamic setup with electron beam diagnostics for the jet density measurements. The results of the experimental modeling for the nozzles of various diameters confirm that a key parameter determining

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11

Degond, Pierre, and Min Tang. "All Speed Scheme for the Low Mach Number Limit of the Isentropic Euler Equations." Communications in Computational Physics 10, no. 1 (2011): 1–31. http://dx.doi.org/10.4208/cicp.210709.210610a.

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AbstractAn all speed scheme for the Isentropic Euler equations is presented in this paper. When the Mach number tends to zero, the compressible Euler equations converge to their incompressible counterpart, in which the density becomes a constant. Increasing approximation errors and severe stability constraints are the main difficulty in the low Mach regime. The key idea of our all speed scheme is the special semi-implicit time discretization, in which the low Mach number stiff term is divided into two parts, one being treated explicitly and the other one implicitly. Moreover, the flux of the d

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Auddy, Sayantan, Shantanu Basu, and Takahiro Kudoh. "The Magnetic Field versus Density Relation in Star-forming Molecular Clouds." Astrophysical Journal Letters 928, no. 1 (2022): L2. http://dx.doi.org/10.3847/2041-8213/ac5a5a.

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Abstract We study the magnetic field to density (B–ρ) relation in turbulent molecular clouds with dynamically important magnetic fields using nonideal three-dimensional magnetohydrodynamic simulations. Our simulations show that there is a distinguishable break density ρ T between the relatively flat low-density regime and a power-law regime at higher densities. We present an analytic theory for ρ T based on the interplay of the magnetic field, turbulence, and gravity. The break density ρ T scales with the strength of the initial Alfvén Mach number  A 0 for sub-Alfvénic (  A 0 < 1 ) and tr

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13

Radhakrishnan P, Ramanan G, Chandan Gowda H R, Meghana C K, and Chaithra A N. "Aerodynamic Performance Analysis of a Variable Sweep Wing for Commercial Aircraft Applications." ACS Journal for Science and Engineering 1, no. 1 (2021): 31–37. http://dx.doi.org/10.34293/acsjse.v1i1.5.

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This study presents a detailed study on wing and its configurations and the morphing techniques for the wing. The morphing methods of the wing such as variable chord, variable span variable cambers have been studied in detail. In this study in detail about the effects of morphable sweep wing, the commercial aircraft wing has been designed and it‘s been modelled using the solid works software. To study the aerodynamic performance the wing, the wing has been analysed in ANSYS Fluent software and the results are interpreted in detail to analyze the effect of wing and its shapes. From the results

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14

Wang, L., Y. Zhao, and S. Fu. "Computational study of drag increase due to wall roughness for hypersonic flight." Aeronautical Journal 121, no. 1237 (2017): 395–415. http://dx.doi.org/10.1017/aer.2017.9.

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ABSTRACTIn this study, a series of numerical experiments are performed on supersonic/hypersonic flows over an adiabatic flat plate with transitionally and fully rough surfaces. The Mach numbers simulated are 4, 5, 6, and 7; the flight heights considered are 20, 24, 28, 32, and 36 km. First, a modified roughness correction is proposed and validated with the measured data for low-speed flat-plate cases. It is verified that for the equivalent sand grain heights in the intermediate and fully rough regimes, there is a good agreement with the semi-empirical formula available in the open literature.

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15

Chalons, Christophe, Mathieu Girardin, and Samuel Kokh. "An All-Regime Lagrange-Projection Like Scheme for the Gas Dynamics Equations on Unstructured Meshes." Communications in Computational Physics 20, no. 1 (2016): 188–233. http://dx.doi.org/10.4208/cicp.260614.061115a.

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AbstractWe propose an all regime Lagrange-Projection like numerical scheme for the gas dynamics equations. By all regime, we mean that the numerical scheme is able to compute accurate approximate solutions with an under-resolved discretization with respect to the Mach number M, i.e. such that the ratio between the Mach number M and the mesh size or the time step is small with respect to 1. The key idea is to decouple acoustic and transport phenomenon and then alter the numerical flux in the acoustic approximation to obtain a uniform truncation error in term of M. This modified scheme is conser

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16

Meng, Jianping, Yonghao Zhang, Nicolas G. Hadjiconstantinou, Gregg A. Radtke, and Xiaowen Shan. "Lattice ellipsoidal statistical BGK model for thermal non-equilibrium flows." Journal of Fluid Mechanics 718 (February 8, 2013): 347–70. http://dx.doi.org/10.1017/jfm.2012.616.

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AbstractA thermal lattice Boltzmann model is constructed on the basis of the ellipsoidal statistical Bhatnagar–Gross–Krook (ES-BGK) collision operator via the Hermite moment representation. The resulting lattice ES-BGK model uses a single distribution function and features an adjustable Prandtl number. Numerical simulations show that using a moderate discrete velocity set, this model can accurately recover steady and transient solutions of the ES-BGK equation in the slip-flow and early transition regimes in the small-Mach-number limit that is typical of microscale problems of practical interes

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17

Galié, Thomas, Jonathan Jung, Ibtissem Lannabi, and Vincent Perrier. "Extension of an all-Mach Roe scheme able to deal with low Mach acoustics to full Euler system." ESAIM: Proceedings and Surveys 76 (2024): 35–51. http://dx.doi.org/10.1051/proc/202476035.

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We propose to extend the fix of Roe’s approximate Riemann solver developed for the Barotropic Euler equations in [2] to the full Euler equations. This scheme is built mainly to handle low Mach acousticwaves. Moreover, compared to pressure-centered type schemes, this numerical fix has the advantage of improving the numerical solution in the sense that the oscillating modes are reduced. The theoretical study is based on a two-time scales asymptotic analysis. It is proved that the Euler system equipped with a general equation of state is consistent with a first-order wave system in a low Mach num

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18

Wang, Meng, Yi Liu, and Kan Wang. "Wall-pressure fluctuations in weakly compressible turbulent channel flow." Journal of the Acoustical Society of America 154, no. 4_supplement (2023): A282. http://dx.doi.org/10.1121/10.0023529.

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Wall-pressure fluctuations in turbulent wall-bounded flows are detrimental in many applications because they can cause structural vibrations and acoustic radiation. Their spectral behavior at subconvective wavenumbers are to date poorly understood and predicted, particularly in low-Mach-number flows. In this study, compressible direct numerical simulation is employed to elucidate the low-wavenumber behavior of wall-pressure fluctuations in turbulent channel flow and the effect of flow Mach number in the nearly incompressible regime. Simulations are conducted at bulk Mach numbers of 0.4, 0.2, a

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Rubin, T., E. J. Kolmes, I. E. Ochs, M. E. Mlodik, and N. J. Fisch. "Fueling limits in a cylindrical viscosity-limited reactor." Physics of Plasmas 29, no. 8 (2022): 082302. http://dx.doi.org/10.1063/5.0101271.

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Recently, a method to achieve a “natural hot-ion mode” was suggested by utilizing ion viscous heating in a rotating plasma with a fixed boundary. We explore the steady-state solution to the Braginskii equations and find the parameter regime in which a significant temperature difference between ions and electrons can be sustained in a driven steady state. The threshold for this effect occurs at [Formula: see text]. An analytic, leading order low flow solution is obtained, and a numerical, moderate Mach number [Formula: see text] is investigated. The limitation is found to be at moderate Mach nu

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20

Alam, Mahbub, and Paul L. Voss. "Graphene quantum interference photodetector." Beilstein Journal of Nanotechnology 6 (March 12, 2015): 726–35. http://dx.doi.org/10.3762/bjnano.6.74.

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In this work, a graphene quantum interference (QI) photodetector was simulated in two regimes of operation. The structure consists of a graphene nanoribbon, Mach–Zehnder interferometer (MZI), which exhibits a strongly resonant transmission of electrons of specific energies. In the first regime of operation (that of a linear photodetector), low intensity light couples two resonant energy levels, resulting in scattering and differential transmission of current with an external quantum efficiency of up to 5.2%. In the second regime of operation, full current switching is caused by the phase decoh

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21

Barsukow, Wasilij, Philipp V. F. Edelmann, Christian Klingenberg, Fabian Miczek, and Friedrich K. Röpke. "A Numerical Scheme for the Compressible Low-Mach Number Regime of Ideal Fluid Dynamics." Journal of Scientific Computing 72, no. 2 (2017): 623–46. http://dx.doi.org/10.1007/s10915-017-0372-4.

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22

Zou, Ziqiang, Edouard Audit, Nicolas Grenier, and Christian Tenaud. "An Accurate Sharp Interface Method for Two-Phase Compressible Flows at Low-Mach Regime." Flow, Turbulence and Combustion 105, no. 4 (2020): 1413–44. http://dx.doi.org/10.1007/s10494-020-00125-1.

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23

Li, Xiang-Yu, and Lars Mattsson. "Coagulation of inertial particles in supersonic turbulence." Astronomy & Astrophysics 648 (April 2021): A52. http://dx.doi.org/10.1051/0004-6361/202040068.

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Coagulation driven by supersonic turbulence is primarily an astrophysical problem because coagulation processes on Earth are normally associated with incompressible fluid flows at low Mach numbers, while dust aggregation in the interstellar medium for instance is an example of the opposite regime. We study coagulation of inertial particles in compressible turbulence using high-resolution direct and shock-capturing numerical simulations with a wide range of Mach numbers from nearly incompressible to moderately supersonic. The particle dynamics is simulated by representative particles and the ef

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van Marle, Allard Jan. "On the influence of supra-thermal particle acceleration on the morphology of low-Mach, high-β shocks". Monthly Notices of the Royal Astronomical Society 496, № 3 (2020): 3198–208. http://dx.doi.org/10.1093/mnras/staa1771.

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ABSTRACT When two galaxy clusters encounter each other, the interaction results in a collisionless shock that is characterized by a low (1–4) sonic Mach number, and a high-Alfvénic Mach number. Our goal is to determine if, and to what extent, such shocks can accelerate particles to sufficient velocities that they can contribute to the cosmic ray spectrum. We combine two different computational methods, magnetohydrodynamics (MHD) and particle-in-cell (PIC) into a single code that allows us to take advantage of the high computational efficiency of MHD while maintaining the ability to model the b

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Eiximeno, Benet, Carlos Tur-Mongé, Oriol Lehmkuhl, and Ivette Rodríguez. "Hybrid Computation of the Aerodynamic Noise Radiated by the Wake of a Subsonic Cylinder." Fluids 8, no. 8 (2023): 236. http://dx.doi.org/10.3390/fluids8080236.

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The noise radiated by the flow around a cylinder in the subcritical regime at ReD=1×104 and at a subsonic Mach number of M=0.5 is here studied. The aerodynamic sound radiated by a cylinder has been studied with a wide range of Reynolds numbers, but there are no studies about how the Mach number affects the acoustic field in the subsonic regime. The flow field is resolved by means of large-eddy simulations of the compressible Navier–Stokes equations. For the study of the noise propagation, formulation 1C of the Ffowcs Williams–Hawkings analogy is used. The fluid flow results show good agreement

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Huet, Maxime, and Alexis Giauque. "A nonlinear model for indirect combustion noise through a compact nozzle." Journal of Fluid Mechanics 733 (September 23, 2013): 268–301. http://dx.doi.org/10.1017/jfm.2013.442.

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AbstractThe present paper deals with the generation of sound by the passage of acoustic or entropy perturbations through a nozzle in the nonlinear regime and in the low-frequency limit. The analytical model of Marble and Candel for compact nozzles (J. Sound Vib., vol. 55, 1977, pp. 225–243), initially developed for excitations in the linear regime, is rederived and extended to the nonlinear domain. Full nonlinear and second-order models are written for both subcritical and supercritical nozzles in the absence of shock and a detailed methodology is provided for the resolution of the second-orde

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27

Gat, Ilana, Georgios Matheou, Daniel Chung, and Paul E. Dimotakis. "Incompressible variable-density turbulence in an external acceleration field." Journal of Fluid Mechanics 827 (August 24, 2017): 506–35. http://dx.doi.org/10.1017/jfm.2017.490.

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Dynamics and mixing of a variable-density turbulent flow subject to an externally imposed acceleration field in the zero-Mach-number limit are studied in a series of direct numerical simulations. The flow configuration studied consists of alternating slabs of high- and low-density fluid in a triply periodic domain. Density ratios in the range of $1.05\leqslant R\equiv \unicode[STIX]{x1D70C}_{1}/\unicode[STIX]{x1D70C}_{2}\leqslant 10$ are investigated. The flow produces temporally evolving shear layers. A perpendicular density–pressure gradient is maintained in the mean as the flow evolves, wit

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Doshi, Parshwanath S., Rajesh Ranjan, and Datta V. Gaitonde. "Global and local modal characteristics of supersonic open cavity flows." Physics of Fluids 34, no. 3 (2022): 034104. http://dx.doi.org/10.1063/5.0082808.

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Flows past cavities at high-speeds have become increasingly important in applications such as flame-holding and propulsion unstart control. Recently maturated linear techniques have helped discern the underlying mechanisms in the subsonic and low supersonic speed regime ([Formula: see text]). Here, we combine these linear methods with fully non-linear two- and three-dimensional simulations to assimilate the significant changes observed when the Mach number is increased further to the [Formula: see text] range. The resolvent method is first employed to analyze cavity-shear layer coupled oscilla

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CHANG, KEH-CHIN, and WEN-CHUNG WU. "A STUDY ON FLOW REGIME NEAR CRITICAL RAYLEIGH NUMBER FOR BUOYANCY-DRIVEN CAVITY FLOW." Modern Physics Letters B 19, no. 28n29 (2005): 1635–38. http://dx.doi.org/10.1142/s0217984905010098.

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A benchmark problem with air medium in a square cavity heated by a vertical side is studied in a Ra range near its critical value without using the usual model approximations, such as Boussinesq or low-Mach-number approximation. Two analysis methods of power spectrum and phase trajectory are adopted to distinguish the flow pattern in the cavity. It demonstrates how the flow evolves from transition to turbulent regimes with increasing Ra values.

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Tabrizi, Amir Bashirzadeh, and Binxin Wu. "The role of compressibility in computing noise generated at a cavitating orifice." International Journal of Aeroacoustics 18, no. 1 (2018): 73–91. http://dx.doi.org/10.1177/1475472x18812801.

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The computational fluid dynamics calculation can be accomplished by solving either compressible or incompressible Navier–Stokes equations to determine the flow-field variables of the noise source. The proper assumption depends on both the physical situation and the Mach number. Although in cavitating devices usually we are dealing with low Mach number flow, cavitation is an acoustic phenomenon that can be affected by compressibility. Cavitation behaves acoustically as a monopole and it is mentioned by some researchers that incompressible solution is sufficient to study the dipole sources. Howe

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31

Vera, M., H. P. Hodson, and R. Vazquez. "The Effects of a Trip Wire and Unsteadiness on a High-Speed Highly Loaded Low-Pressure Turbine Blade." Journal of Turbomachinery 127, no. 4 (2004): 747–54. http://dx.doi.org/10.1115/1.1934446.

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This paper presents the effect of a single spanwise two-dimensional wire upon the downstream position of boundary layer transition under steady and unsteady inflow conditions. The study is carried out on a high turning, high-speed, low pressure turbine (LPT) profile designed to take account of the unsteady flow conditions. The experiments were carried out in a transonic cascade wind tunnel to which a rotating bar system had been added. The range of Reynolds and Mach numbers studied includes realistic LPT engine conditions and extends up to the transonic regime. Losses are measured to quantify

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Proença, A. R., O. De almeida, and R. H. Self. "AERODYNAMICS AND AEROACOUSTICS SURVEY FOR A LOW SPEED SUBSONIC JET OPERATING AT MACH 0.25." Revista de Engenharia Térmica 13, no. 2 (2014): 33. http://dx.doi.org/10.5380/reterm.v13i2.62092.

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The purpose of this work is to study and characterize, in laboratory, the aerodynamics of a free jet operating at subsonic regime and identify its acoustic signature. This study aims to analyze the fundamental role of turbulent flow structures in the total noise produced at different Mach numbers. This work is focused at low speed subsonic jets operating at Mach number 0.25. The research is done by analyzing the data obtained in experiments using Pitot tube, hot-wire anemometer and acoustic measurements. This work also describes the experimental procedures for each step of analysis, as well as

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Tahani, Mojtaba, Mohammad Hojaji, and Seyed Vahid Mahmoodi Jezeh. "Turbulent jet in crossflow analysis with LES approach." Aircraft Engineering and Aerospace Technology 88, no. 6 (2016): 717–28. http://dx.doi.org/10.1108/aeat-10-2014-0167.

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Purpose This study aims to investigate effects of sonic jet injection into supersonic cross-flow (JISC) numerically in different dynamic pressure ratio values and free stream Mach numbers. Design/methodology/approach Large Eddy simulation (LES) with dynamic Smagorinsky model is used as the turbulence approach. The numerical results are compared with the experimental data, and the comparison shows acceptable validation. Findings According to the results, the dynamic pressure ratio has critical effects on the zone related to barrel shock. Despite free stream Mach number, increasing dynamic press

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Gouasmi, Ayoub, Scott M. Murman, and Karthik Duraisamy. "Entropy-stable schemes in the low-Mach-number regime: Flux-preconditioning, entropy breakdowns, and entropy transfers." Journal of Computational Physics 456 (May 2022): 111036. http://dx.doi.org/10.1016/j.jcp.2022.111036.

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Kalita, B. C., та N. Devi. "Kinetic Alfvén solitons in a low-β plasma under the influence of electron drift motion". Journal of Plasma Physics 56, № 1 (1996): 35–44. http://dx.doi.org/10.1017/s0022377800019073.

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Fully nonlinear kinetic Alfvén solitary waves are investigated, taking account of the drifting effect of electrons in the direction of the external magnetic field in a low-β plasma (where β = 8πn0T/c2B02 is the ratio of the kinetic pressure to the magnetic pressure). Both compressive and rarefactive Alfvén solitons are found to exist in different ranges of kz (direction of wave propagation), depending on the values of M (the Mach number) and ve (the drift velocity, occurring implicitly in an effective parameter A). The existence domain of kinetic Alfvén solitons is found to be concentrated in

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Deng, S., B. W. van Oudheusden, T. Xiao, and H. Bijl. "A Computational Study on the Aerodynamic Influence of a Propeller on an MAV by Unstructured Overset Grid Technique and Low Mach Number Preconditioning." Open Aerospace Engineering Journal 5, no. 1 (2012): 11–21. http://dx.doi.org/10.2174/1874146001205010011.

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The influence of a propeller on the aerodynamic performance of an MAV is investigated using an unstructured overset grid technique. The flow regime of a fixed-wing MAV powered by a propeller contains both incompressible regions due to the low flight speed, as well as compressible flow areas near the propeller-tip region. In order to simulate all speed flow efficiently, a dual-time preconditioning method is employed in the present study. The methodology in this paper is verified as providing a reliable numerical simulation tool for all flow regimes, in the additional presence of moving boundari

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Khayat, Roger E., and Byung Chan Eu. "Generalized hydrodynamics and linear stability analysis of cylindrical Couette flow of a dilute Lennard–Jones fluid." Canadian Journal of Physics 71, no. 11-12 (1993): 518–36. http://dx.doi.org/10.1139/p93-081.

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Linear stability analysis is carried out for cylindrical Couette flow of a Lennard–Jones fluid in the density range from the dense liquid to the dilute gas regime. Generalized hydrodynamic equations are used to calculate marginal stability curves and compare them with those obtained by using the Navier–Stokes–Fourier equations for compressible fluids and also for incompressible fluids. In the low Reynolds or Mach number regime, if the Knudsen number is sufficiently low, the marginal stability curves calculated by the generalized hydrodynamic theory coincide, within numerical errors, with those

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Guillon, Kévin, Romane Hélie, and Philippe Helluy. "Stability analysis of the vectorial Lattice-Boltzmann method." ESAIM: Proceedings and Surveys 77 (2024): 46–78. http://dx.doi.org/10.1051/proc/202477046.

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We perform a stability analysis of the Vectorial Lattice-Boltzmann Method (VLBM). The VLBM has been introduced in [1–3, 9, 18]. It is a variant of the LBM with extended stability features: it allows handling compressible flows with shock waves, while the LBM is limited to low-Mach number regime. The stability analysis is based on the Legendre transform theory. We also propose a new tool: the equivalent system analysis, which we conjecture to contains both the stability and the consistency of the VLBM.

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Desjacques, Vincent, Adi Nusser, and Robin Bühler. "Analytic Solution to the Dynamical Friction Acting on Circularly Moving Perturbers." Astrophysical Journal 928, no. 1 (2022): 64. http://dx.doi.org/10.3847/1538-4357/ac5519.

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Abstract We present an analytic approach to the dynamical friction (DF) acting on a circularly moving point mass perturber in a gaseous medium. We demonstrate that, when the perturber is turned on at t = 0, steady state (infinite time perturbation) is achieved after exactly one sound-crossing time. At low Mach numbers  ≪ 1 , the circular-motion steady-state DF converges to the linear-motion, finite time perturbation expression. The analytic results describe both the radial and tangential forces on the perturbers caused by the backreaction of the wake propagating in the medium. The radial forc

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Vilquin, Alexandre, Hamid Kellay, and Jean-François Boudet. "Shock waves induced by a planar obstacle in a vibrated granular gas." Journal of Fluid Mechanics 842 (March 7, 2018): 163–87. http://dx.doi.org/10.1017/jfm.2018.128.

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The low value of the speed of sound in dilute granular media permits the study of the properties of supersonic flows for a wide range of Mach numbers. In this paper, we report the experimental observation of a subsonic–supersonic transition in a vibrated granular gas. The shock fronts studied are obtained by simply pushing a rectangular obstacle into the granular gas for different obstacle velocities. The supersonic regime is characterized by the formation of normal shock waves whose width increases when the Mach number decreases to values close to 1. The bimodal model proposed by Mott-Smith i

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Wu, J. S., S. Y. Chou, U. M. Lee, Y. L. Shao, and Y. Y. Lian. "Parallel DSMC Simulation of a Single Under-Expanded Free Orifice Jet From Transition to Near-Continuum Regime." Journal of Fluids Engineering 127, no. 6 (2005): 1161–70. http://dx.doi.org/10.1115/1.2062807.

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This paper describes the numerical analysis of the flow structure of a single underexpanded argon free jet issuing into a lower-pressure or vacuum environment using the parallel three-dimensional direct simulation Monte Carlo (DSMC) method employing dynamic domain decomposition. Unstructured and tetrahedral solution-based refined mesh depending on the local mean free path is used to improve the resolution of solution. Simulated Knudsen numbers of the stagnation conditions based on orifice diameter, Reynolds numbers based on the conditions at the orifice exit, and stagnation-to-background press

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Dimarco, Giacomo, Raphaël Loubère, Victor Michel-Dansac, and Marie-Hélène Vignal. "Second-order implicit-explicit total variation diminishing schemes for the Euler system in the low Mach regime." Journal of Computational Physics 372 (November 2018): 178–201. http://dx.doi.org/10.1016/j.jcp.2018.06.022.

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Rieper, Felix, and Georg Bader. "The influence of cell geometry on the accuracy of upwind schemes in the low mach number regime." Journal of Computational Physics 228, no. 8 (2009): 2918–33. http://dx.doi.org/10.1016/j.jcp.2009.01.002.

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Yamouni, Sami, Denis Sipp, and Laurent Jacquin. "Interaction between feedback aeroacoustic and acoustic resonance mechanisms in a cavity flow: a global stability analysis." Journal of Fluid Mechanics 717 (February 1, 2013): 134–65. http://dx.doi.org/10.1017/jfm.2012.563.

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AbstractWe perform a global stability analysis of a flow over an open cavity, characterized by a Reynolds number, based on the upstream velocity and the cavity length, of $7500$. We compute base flows and unstable global modes of the flow for different Mach numbers ranging from $0$ to $0. 9$. In the incompressible regime ($M= 0$), we show that the flow is subject to global instabilities due to Kelvin–Helmholtz instabilities in the shear layer, which become strengthened by a hydrodynamic pressure feedback. The influence of the boundary-layer thickness and of the length-to-depth ratio of the cav

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GILL, TARSEM SINGH, HARVINDER KAUR, and NARESHPAL SINGH SAINI. "Dust-acoustic solitary waves in a finite temperature dusty plasma with variable dust charge and two temperature ions." Journal of Plasma Physics 70, no. 4 (2004): 481–95. http://dx.doi.org/10.1017/s0022377803002733.

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In this paper, the characteristics of dust-acoustic solitary waves in dusty plasma are studied. Dust charge and temperature are treated as variables. The authors have used the pseudopotential method to investigate the possibility of compressive as well as rarefactive solitons. An expression for the pseudopotential has been derived. The pseudopotential is a function of the Mach number, the relative temperature of low and high ion components, the relative ion concentration of dust charge and the temperature. Numerical computation shows that for the chosen set of parameters, only compressive soli

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Yan, Chian, Hong Hui Teng, Xiao Cheng Mi, and Hoi Dick Ng. "The Effect of Chemical Reactivity on the Formation of Gaseous Oblique Detonation Waves." Aerospace 6, no. 6 (2019): 62. http://dx.doi.org/10.3390/aerospace6060062.

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High-fidelity numerical simulations using a Graphics Processing Unit (GPU)-based solver are performed to investigate oblique detonations induced by a two-dimensional, semi-infinite wedge using an idealized model with the reactive Euler equations coupled with one-step Arrhenius or two-step induction-reaction kinetics. The novelty of this work lies in the analysis of chemical reaction sensitivity (characterized by the activation energy Ea and heat release rate constant kR) on the two types of oblique detonation formation, namely, the abrupt onset with a multi-wave point and a smooth transition w

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Collé, Anthony, Jérôme Limido, and Jean-Paul Vila. "An Accurate SPH Scheme for Dynamic Fragmentation modelling." EPJ Web of Conferences 183 (2018): 01030. http://dx.doi.org/10.1051/epjconf/201818301030.

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We focus on the use of a meshless numerical method called Smooth Particle Hydrodynamics (SPH), to solve fragmentation issues as Hyper Velocity Impact (HVI) cases. Firstly applied to fluid flow simulations, this method can be extended to the solid dynamics framework. However it suffers from a lack of accuracy when evaluating state variables as the pressure field. And such inaccuracy generally generates non-physical processes (as numerical fragmentation). In the hydrodynamic context, SPH-ALE methods based on Riemann solvers significantly improve this evaluation, but increase the scheme complexit

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Feireisl, Eduard, Mária Lukáčová-Medviďová, Šárka Nečasová, Antonín Novotný, and Bangwei She. "Asymptotic Preserving Error Estimates for Numerical Solutions of Compressible Navier--Stokes Equations in the Low Mach Number Regime." Multiscale Modeling & Simulation 16, no. 1 (2018): 150–83. http://dx.doi.org/10.1137/16m1094233.

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MAYER, CHRISTIAN S. J., DOMINIC A. VON TERZI, and HERMANN F. FASEL. "Direct numerical simulation of complete transition to turbulence via oblique breakdown at Mach 3." Journal of Fluid Mechanics 674 (January 13, 2011): 5–42. http://dx.doi.org/10.1017/s0022112010005094.

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A pair of oblique waves at low amplitudes is introduced in a supersonic flat-plate boundary layer at Mach 3. Its downstream development and the concomitant process of laminar to turbulent transition is then investigated numerically using linear-stability theory, parabolized stability equations and direct numerical simulations (DNS). In the present paper, the linear regime is studied first in great detail. The focus of the second part is the early and late nonlinear regimes. It is shown how the disturbance wave spectrum is filled up by nonlinear interactions and which flow structures arise and

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Theofanous, T. G., G. J. Li, and T. N. Dinh. "Aerobreakup in Rarefied Supersonic Gas Flows." Journal of Fluids Engineering 126, no. 4 (2004): 516–27. http://dx.doi.org/10.1115/1.1777234.

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We present new experimental results on the interfacial instabilities and breakup of Newtonian liquid drops suddenly exposed to rarefied, high-speed (Mach 3) air flows. The experimental approach allows for the first time detailed observation of interfacial phenomena and mixing throughout the breakup cycle over a wide range of Weber numbers. Key findings are that Rayleigh-Taylor instability alone is the active mechanism for freestream Weber numbers as low as 28 for low viscosity liquids and that stripping rather than piercing is the asymptotic regime as We→∞. This and other detailed visual evide

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