斜切反喷管性能分析

固体火箭发动机前端斜切反喷管，其结构简单、作用时间短、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。本文从雷诺平均的非定常Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程出发，结合采用Ｂｏｌｄｗｉｎ－Ｌｏｍａｘ代数湍流模型，利用时间相关法及ＭａｃＯｃｏｒｍａｒｋ两步显格式求解，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布相一致。该方法可应用于斜切反喷管的

Performance Analysis of the Scarfed Reversal Nozzle in Solid Rocket Motor

The scarfed reversal nozzle on the forward of the motor has a very short actual time and its simple configuration. Its gasdynamic contours have many discontinuous point and a step at supersonic zone. So a series of shock wave and flows separation exists in flow field of the reversal nozzle. Renolds average unsteady Navier Stokes equations with Baldwin Lomax algebraical turbulent model are employed to simulate the flow field in a scarfed reversal nozzle. The governing equation in general curvilinear coordinates are numerically solved by using time dependent method and utilizing MacCormack scheme. The flow field of the scarfed reversal nozzle is calculated. The calculated wall pressure distributions are in good agreement with experimental data by wind tunnel. The method is avaliable to predict the performance of the scarfed reversal nozzle.