固体火箭技术2011，Vol.34Issue(4)：418-422,5.
基于RANS/NLAS的火箭跨声速脉动压力环境预示
A prediction of fluctuation pressure conditions with transonic rocket by RANS/NLAS method
摘要
Abstract
In order to predict the fluctuating-pressure conditions with large-scale rocket rapidly and accurately, a combined approach with the Reynolds-averaged Navier Stokes ( RANS) solved for flow field and the Non-linear Acoustics Solver ( NLAS) for acoustical field was applied.The numerical solutions of the fluctuating pressures typically at cone-cylinder shoulder、 stem inverted cone,skirt-cylinder shoulder of rocket in transonic flow were shown,and the root-mean-square fluctuating pressure coefficients and sound pressure levels with various mach numbers were given. The results indicate that the RANS/NLAS method combined with twoequation non-linear κ-ε turbulence model, far-field absorbing boundary condition and wall function can be successfully used in solving fluctuating pressure conditions with a transonic rocket; the fluctuating pressure at inverted cone is more serious than those at cone-cylinder and skirt-cylinder,and at inverted cone is the most serions fluctuation pressure encountered in flow with Mach number from 0.9 to 0.975; the energy of fluctuating pressure is almost in low frequency( about 100 Hz ).关键词
跨声速流/RANS/NLAS/脉动压力/声压级Key words
transonic flow/RANS/NLAS/fluctuation pressure/sound pressure level分类
航空航天引用本文复制引用
任淑杰,张收运,闫桂荣..基于RANS/NLAS的火箭跨声速脉动压力环境预示[J].固体火箭技术,2011,34(4):418-422,5.基金项目
国防973资助项目(61355). （61355）
