自吸气脉冲爆震发动机超声速进气道气动性能的数值研究

采用有限体积法计算了某轴对称超声速进气道,在不同幅度和频率的出口扰动压强下的进气道内结尾正激波的运动情况,得出了进气道内结尾正激波运动特性和扰动压强的频率和幅度的关系。在计算中,本文采用了多块结构化网格,控制体积的界面无粘通量采用三阶迎风格式插值获得,同时采用了minmod通量限制器,以确保在激波处的解的物理特性;扩散通量采用二阶中心差分格式插值获得。定常计算采用当地时间步法,非定常计算采用双时间步法。离散的代数方程采用交替方向迭代法求解。

Numerical Study of the Dynamics Performance of a Supersonic Inlet for Air-Breathing Pulse Detonation Engine

A series of numerical computation have been conducted to characterize the movement of the terminal shock inside an axisymmetric supersonic inlet under perturbation pressure with different amplitudes and frequencies. The relationship between the movement of terminal shock and the amplitudes and frequencies of perturbation pressure is demonstrated. The governing equations are discretized by finite volume method. The inviscid flux at the interfaces of control volumes is calculated using 3rd order upwind interpolation, while the corresponding viscous flux is obtained using 2nd order centered difference scheme. The minmod limiter is introduced to eliminate the non-physical elements of solutions. For steady computation, local time step method is used; for unsteady computation, dual time stepping method is used. The discretized algebraic equations are solved using alternate direction iteration method.