Numerical simulation of high speed reacting shear layers using AUSM+-up scheme-based unstructured finite volume method solver
作者机构：Department of Aerospace Engineering Indian Institute of Space Science and Technology ThiruvananthapuramKeralaIndia-695547 Department of Mechanical Engineering SCT College of Engineering ThiruvananthapuramKeralaIndia-695018
出 版 物：《International Journal of Modeling, Simulation, and Scientific Computing》 (建模、仿真和科学计算国际期刊（英文）)
年 卷 期：2017年第8卷第3期
页 面：39-60页
核心收录：
学科分类：080704[工学-流体机械及工程] 080103[工学-流体力学] 08[工学] 0807[工学-动力工程及工程热物理] 0801[工学-力学（可授工学、理学学位）]
主 题：Supersonic combustion turbulent reacting flows advection upstream splitting method
摘 要：Development of an Advection Upstream Splitting Method(AUSM+-up)scheme-based Unstructured Finite Volume(UFVM)solver for the simulation of two-dimensional axisymmetric/planar high speed compressible turbulent reacting shear layers is *** inviscid numerical flux is evaluated using AUSM+-up upwind *** eight-step hydrogen–oxygen finite rate chemistry model is used to model the development of chemical species in a supersonic reacting flow *** chemical species terms are alone solved implicitly in this explicit flow solver by rescaling the equation in *** turbulence modeling has been done using RNG-based k–***-stage Runge–Kutta method has been used for explicit time *** nonreacting twodimensional Cartesian version of the same solver has been successfully validated against experimental and numerical results reported for the wall static pressure data in sonic slot injection to supersonic *** validation studies for reacting flow solver has been done using experimental results reported for a coaxial supersonic combustor,in which species profile at various axial locations has been *** numerical solver is useful in simulating combustors of high speed air-breathing propulsion devices.
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