摘要
为了在级间分离期间提供反推力,许多固体火箭发动机前端都装有一组斜切反喷管,由于反喷管气动型面具有尖点,并在超音速区有台阶,喷管内存在一系列激波,并伴有流动分离现象。从雷诺平均的非定常Navier-Stokes方程出发,利用时间相关法,采用MacCormack两步显格式,结合Baldwin-Lomax代数湍流模型,数值模拟了斜切反喷管流场。计算得到的壁面压强分布与风洞吹风实验测得的压强分市相当一致。
any solid propellant motors use a set of scrafed reversal nozzles located on the forward of the motors to provide reversal thrust during staging. Because the gasdynamic contour of reversal nozzle is not smooth and has a step in supersonic flow region, a series of shocks and flows separation in boundary-layer exists in flowfield of reversal nozzle. The viscous flowfields in scrafed reversalnozzle are simulated based on Renolds--average unsteady Navier--Stokes equations, with time-dependent method, MacCormack explicit scheme and Baldwin-Lomax algebraical turbulent model. Thepressure distributions obtained from computation are in good agreement with experimental data.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1996年第1期24-25,共2页
Journal of Propulsion Technology
关键词
推力反向
喷管
计算流体动力学
火箭发动机
Thrust reversal, Unconventional nozzle,Computational fluid dynamics, Numericalsimulation