The results of a parametric, numerical study of aftbody exhaust flows on a conical, airbreathing, hypersonic vehicle are presented. Three-dimensional Euler simulations were performed at Mach 9 and steered to a pitch-trimmed lift-equals-weight condition. Quasi-1-D cycle analysis was employed to model the scramjet propulsion and viscous forces were accounted for using a separate boundary-layer code. The simulation method is presented and credibility demonstrated before parameters controlling the aftbody design and their effect on vehicle performance are reviewed. The parameter sweep resulted in a wide range of predicted performance (thrust-to-drag ratios of 1.17 to 1.79) with 3-D flow features, interaction between engine modules, and trim penalties identified as strong drivers. The large variation in the thrust-to-drag ratio observed in the results of this study highlights the criticality of the aftbody design of an accelerator.

提出了在圆锥形，呼吸式，高超声速飞行器上进行的尾气排放流量的参数化数值研究的结果。在9马赫速度下进行了三维Euler模拟，并转向了节距修剪的升力-等重条件。准1-D循环分析用于建模超燃冲压发动机的推进，并使用单独的边界层代码来计算粘性力。在回顾了控制车身设计的参数及其对车辆性能的影响之前，提出了仿真方法并证明了其可靠性。参数扫描可产生广泛的预测性能（推力与阻力比为1.17至1.79），并具有3-D流动特性，发动机模块之间的相互作用以及被认为是强力驱动因素的油门罚款。