火箭发动机塞式喷管流场的数值研究

推进技术 ›› 2000, Vol. 21 ›› Issue (5): 19-21.

火箭发动机塞式喷管流场的数值研究

宋明德,张涵信,刘金合

北京航空航天大学国家计算流体力学实验室!北京100083;北京航空航天大学国家计算流体力学实验室!北京100083;北京航空航天大学国家计算流体力学实验室!北京100083

发布日期:2021-08-15
基金资助:
国家自然科学基金;国家博士后科学基金资助项目

Numerical study on plug nozzle flow field

National Laboratory for Computational Fluid Dynamics,Beijing Univ of Aeronautics and Astronautics,Beijing 100083,China;National Laboratory for Computational Fluid Dynamics,Beijing Univ of Aeronautics and Astronautics,Beijing 100083,China;National Laboratory for Computational Fluid Dynamics,Beijing Univ of Aeronautics and Astronautics,Beijing 100083,China

Published:2021-08-15

摘要/Abstract

摘要： 用时间相关法和张涵信的无振荡、无自由参数NND显式格式 ,对火箭发动机塞式喷管二维轴对称定常流场进行了数值模拟。计算得到了有粘和无粘两种情况下 ,喷管流场的马赫数、压强、温度、流线以及速度矢量分布图。计算网格采用代数方法生成 ,并通过求解Laplace方程对网格进行修正。计算结果表明 :NND格式用于计算塞式喷管流场具有较高的效率和良好的分辨率 ;无粘和有粘情况得到的流场结构有较大的差别 ;基础喷管的出口马赫数和总压对流场结构有较大影响。

关键词: 火箭发动机;塞式喷管;数值仿真;计算流体动力学

Abstract: Zhang’s Non oscillatory, Non free parameter Dissipative (NND) explicit scheme was applied to the analysis of inviscid and viscous axisymmetric steady plug nozzle flow field by time dependent method Contours of Mach number, pressure, temperature and velocity vector distribution were obtained The grid mesh for the calculation was generated by algebra method in conjunction with solving Laplace equation to improve the mesh quality Calculation results show that NND scheme is efficient in the numerical simulation for plug nozzle flow field Calculation results also indicate that the inviscid flow structure is quite different from that of the viscous one, and the exit Mach number and total pressure of the base nozzle highly affects the nozzle flow structure

Key words: Rocked engine;Plug nozzle;Numerical simulation;Computational fluid dynamics

宋明德,张涵信,刘金合. 火箭发动机塞式喷管流场的数值研究[J]. 推进技术, 2000, 21(5): 19-21.