摘要
本文从Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程出发，采用先进的矢通量分裂算法，对二维轴对称固体火箭发动机燃烧室及喷管的内流场进行了一体化数值模拟，其中耦合进了燃面侵蚀燃烧的加质作用。计算中对超音速为主的流动进行了抛物化处理，对不同格式对亚跨超音速混合流场的适用情况进行了数值试验。本文除了给出主要的内流场参数预示结果外。
This paper solves the Navier Stokes equation by the advanced flux vector splitting algorithems to simulate the whole flowfield of solid propellant rocket motor chamber and nozzle 2 D axisymmetric internal flow coupled with the erosive burning and mass addition on the burning surface of the grain The parabolized Navier Stokes procedures are used for the predominantly supersonic flowfield,and some numerical tests are made to determine the suitabilities of different schemes for subsonic,transonic and supersonic mixed flow Except some computed flowfield parameters' profiles are given here,the predicted erosive burning results are compaired to the test results
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1997年第1期47-54,共8页
Journal of Astronautics
基金
航空科学基金资助
关键词
固体火箭发动机
侵蚀燃烧
流场
Solid Propellant Rocket Engines Erosive Burning Flowfield Flux Vector Splitting Computer Codes
