ESAIM: Proceedings and Surveys, 2015 We introduce continuous tools to study the low Mach number behavior of the Godunov scheme applied to the linear wave equation with porosity on cartesian meshes.
Dellacherie Stéphane +2 more
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Aerodynamic Parameters Analysis of Transonic Flow Past Unswept and Swept Wings [PDF]
Engineering and Technology Journal, 2011 The transonic flow past unswept and swept wings has been studied. For this purpose the transonic potential flow equation is solved for inviscid compressible flow. The shock waves are replaced by discontinuities across which the entropy is conserved.
Raad Shehab Ahmed
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Note on the limits to the local Mach number on an aerofoil in subsonic flow [PDF]
, 1948 It has been noted in some experiments that the local Mach number just ahead of a shock wave on an aerofoil in subsonic flow is limited, values of the limit of the order of 1.4 are usually quoted.
Young, A. D.
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On a diphasic low mach number system [PDF]
ESAIM: Mathematical Modelling and Numerical Analysis, 2005 The author proposes a diphasic low Mach number (DLMN) system for the modelling of diphasic flows at low Mach number. This system filters out the acoustic waves but keeps all the informations coming from the thermodynamic as the equations of state and the entropy contrary to a standard incompressible diphasic Navier-Stokes system.
openaire +1 more source
A universal scaling law for the evolution of granular gases
, 2015 Dry, freely evolving granular materials in a dilute gaseous state coalesce into dense clusters only due to dissipative interactions. This clustering transition is important for a number of problems ranging from geophysics to cosmology.
Clewett, James P. D. +2 more
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A Simple Modification of HLLEM Approximate Riemann Solver Applied to the Compressible Euler System at Low Mach Number [PDF]
, 2020 Hang Yu, Hua Li, Jianqi Lai, Ye Zhang
openalex +1 more source
Simulations of the Galaxy Cluster CIZA J2242.8+5301 I: Thermal Model and Shock Properties [PDF]
, 2017 The giant radio relic in CIZA J2242.8+5301 is likely evidence of a Mpc sized shock in a massive merging galaxy cluster. However, the exact shock properties are still not clearly determined. In particular, the Mach number derived from the integrated radio
Beck, A. M. +3 more
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Numerical Analysis of Supersonic Film Cooling in Supersonic Flow in Hypersonic Inlet with Isolator
Advances in Mechanical Engineering, 2014 Supersonic film cooling is an efficient method to cool the engine with extremely high heat load. In order to study supersonic film cooling in a real advanced engine, a two-dimensional model of the hypersonic inlet in a scramjet engine with supersonic ...
Silong Zhang +3 more
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Low-speed aerodynamic performance of 50.8-centimeter-diameter noise-suppressing inlets for the Quiet, Clean, Short-haul Experimental Engine (QCSEE) [PDF]
Two basic inlet concepts, a high throat Mach number (0.79) design and a low throat Mach number (0.60) design, were tested with four diffuser acoustical treatment designs that had face sheet porosity ranging from 0 to 24 percent for the high Mach number ...
Abbott, J. M. +2 more
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Investigation of Rotor Tip Vortex in Hover Based on IDDES Methods
Xibei Gongye Daxue Xuebao, 2019 A calculation and analysis program of high-precision numerical simulation for rotor blade tip vortex in hovering state was developed. The fifth order Roe-WENO scheme was carried out in order to reduce the numerical dissipation of the rotor wake region ...
doaj +1 more source