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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。
To provide thrust reversal during interstage separation, many solid rocket motors are equipped with a series of chamfered counter-nozzles on the front end. Due to the sharp point of the aerodynamic surface of the counter-nozzle and the step in the supersonic zone, there is a series of shocks in the nozzle Wave, accompanied by the phenomenon of flow separation. Starting from the Reynolds-averaged unsteady Navier-Stokes equations, the time-dependent method was used to numerically simulate the flow field of the beveled anti-nozzle by using the MacCormack two-step format and the Baldwin-Lomax algebraic turbulence model. The calculated wall pressure distribution is quite consistent with the pressure measured by the wind tunnel blowing experiment.