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 引用本文: 王丁喜, 严传俊. 脉冲爆震发动机进气道气动性能的数值研究[J]. 力学学报, 2005, 37(6): 777-782.
Numerical study of the dynamics performance of the supersonic inlet for air-breathing pulse detonation engine[J]. Chinese Journal of Theoretical and Applied Mechanics, 2005, 37(6): 777-782.
 Citation: Numerical study of the dynamics performance of the supersonic inlet for air-breathing pulse detonation engine[J]. Chinese Journal of Theoretical and Applied Mechanics, 2005, 37(6): 777-782.

## Numerical study of the dynamics performance of the supersonic inlet for air-breathing pulse detonation engine

• 摘要: 采用有限体积法计算了脉冲爆震发动机某轴对称超音速进气道在3种不同出口条件(单个正弦扰动压力、某脉冲爆震发动机爆震室头部表压和进气道出口堵塞)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不同出口条件的关系. 在计算中，采用了多块结构化网格，控制体积的界面无黏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。

Abstract: A series of numerical computation have been conducted to characterize the movement of the terminal shock inside an axisymmetric supersonic inlet under different outlet conditions: sinusoidal perturbation pressure, experimental gauge pressure history at the head wall of a PDE and blockage of outlet of inlet. The relationship between the movement of terminal shock and the outlet conditions is demonstrated. The governing equations are discretized by finite volume method. The inviscid flux at the interfaces of control volumes is computed using three order upwind interpolation, while the corresponding viscous flux is computed using two order centered difference scheme. The minmod limiter is introduced to eliminate the non-physical elements of solutions. For steady computation, time-dependent method is used; for unsteady computation, dual time stepping method is used. The discretized algebraic equations are solved using alternate direction iteration method.

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