中文摘要：

以定楔角乘波体设计方法为基础,研究了影响高超/超声速乘波体“乘波”的主要因素,给出了前体前缘实际气流压缩角的确定方法及影响因素,可知在相同的来流马赫数和压缩角δ下,随着前缘角θ和气流与前缘夹角α的增加,实际气流偏转角γ减小。据此,基于幂函数进气道前体构形,给出了前缘激波不脱体的限制条件及具体的判定方法,分析了乘波体典型几何特征参数对前缘激波不脱体的影响规律,结果显示在相同的来流马赫数和压缩角度下,增大前缘形状因子n,减小前体的长宽比L/W及增大前缘角均有利于激波不脱体。根据给出的前体几何参数对前缘激波脱体的影响规律曲线,对一种“前体几何外形构造＋前缘激波附体条件限制”的正向前体乘波器工程设计方法进行了研究,给出了具体设计流程,并进行了初步的数值仿真验证,表明通过该方法设计的乘波前体流动特征与预期的结果吻合,说明文中所给出的激波附体条件及影响规律是可信的,乘波前体设计方法是可行的。

英文摘要：

In this paper,the factor that affects the shock attached forebody was investigated.The results show that,at the same Mach number of inflow and the angle of forebody, with the increasing of the forebody shape gene n and the angle of edge, the shock can attach to the forebody.With the decrease of the length/width（L/W）ratio of forebody, the same phenomenon occurs.Based on the hypersonic 2D inlet forebody, a new concept of ＂geometry configuration＋shock attached forebody limited＂ was studied, and the factor that influences the shock attached to the forebody was investigated and presented.Based on the parametrical study,the design meth- odology and process of waverider controllable forebody were provided.The basic flow characteristics of waverider forebody were ana- lyzed by numerical simulation.The numerical results show that the design method and the limit of shock attached forebody were cred- ible.