高超声速内转式进气道型面流场重构

内转式进气道流场参数分布不均，为改善该类进气道的气动性能，本文采用数值仿真方法开展了基于型面的内转式进气道流场重构研究。结果表明：流场重构型面中心线对进气道流场结构及流动特性影响较大，在给定偏距/长度与中心线末端斜率的约束条件下，选取合适的中心线起始角能够大幅提高进气道的气动性能，改善流场参数分布。与进气道原型方案相比，流场重构型面中心线10°起始角的进气道方案总压恢复系数、抗反压能力最大分别提升33.7%、26.4%，自起动马赫数下降1.1。随着流场重构型面中心线起始角增大，唇罩激波/侧壁边界层干扰诱发的流向涡减弱、流向涡传输轨迹向唇罩一侧偏移，低能流向唇罩两侧迁移趋势增强。在研究范围内，随着流场重构型面中心线起始角增大，隔离段出口总压恢复系数先增大后减小，自起动马赫数先下降后不变。

Flow field reconstruction of hypersonic inward turning inlet based on configuration

The distribution of flow field parameters of inward turning inlet is uneven. In order to improve the aerodynamic performances of inward turning inlet, a numerical simulation method is employed to study the flow field reconstruction of inward inlet based on the configuration. The results show that the centerline of the flow field reconstruction surface largely influences the flow field structure and flow characteristics of inlet. Under the given offset distance/length and slope at the end of centerline, the aerodynamic performances and the distribution of flow field parameters of the inlet at appropriate initial angle of centerline are improved. Compared with the basic inward turning inlet, at centerline initial angle 10°, the total pressure recovery at outlet and the back pressure capability of the inlet improved by 33.7% and 26.4%, and the self-starting Mach number decreased by 1.1. As the initial angle of the centerline increases, the streamwise vortex induced by the shock/sidewall boundary layer interaction weakens and the trajectory of streamwise vortex shifts to the cowl side from ramp, and the migration of flow with low total pressure to cowl on both sides enhances. Within the research scope, as the initial angle of centerline increases, the total pressure recovery of the outlet increases firstly and then decreases, and the self-starting Mach number decreases firstly and then remains constant.