基于前体激波的内转式进气道一体化设计

在腹部进气的乘波前体/内转式进气道的一体化设计中，为使进气道捕获截面和唇口型线的形状与飞行器前体激波较好匹配，提出一种基于前体激波形状的一体化设计方法。首先，计算乘波前体流场并提取前体激波形状；其次，将进气道捕获型线（ICC）投影在前体激波曲面上，得到可全流量捕获的进气道唇口型线（IFCC）；再次，给定进气道基本流场的中心体轴线位置，确定基本流场的入射激波形状；然后，给定基本流场的沿程压缩规律，应用特征线法确定进气道的基本流场；最后，将ICC顺来流方向投影至进气道入射激波曲面上，经流线追踪和黏性修正得到最终的进气道型面。数值模拟结果表明，对于典型飞行器前体，在设计马赫数为7.0的条件下，应用该方法得到的进气道流量捕获系数达0.976，隔离段出口截面的马赫数、压比和总压恢复系数分别为3.17、38.9和0.487。

Integration design of inward-turning inlets based on forebody shock wave

To achieve better matching between the shape of the capture section and inlet entrance line and the forebody shock wave, an integration design method is proposed based on the shape of the forebody shock wave for the integration design of waverider forebody/inward-turning inlet with the intake of abdomen. First, the flow field of the waverider forebody is calculated, and the forebody shock surface is extracted. Second, the Inlet Full Capture Curve (IFCC) is acquired by projecting the Inlet Capture Curve (ICC) on the forebody shock surface. Third, the shape of the incident shock in the basic flow field is determined after the axis of center body is given. Then, the basic flow field is determined by the method of characteristic after the distribution law of the Mach number along the compression boundary is presented. Finally, the inlet lip is obtained through the projection of ICC on the incident shock surface of the inlet in the direction of the incoming flow, and the final inlet surface is obtained through streamline-tracing and viscosity correction. Numerical results show that the inlet mass capture coefficient reaches 0.976 at Mach number 7.0 for a typical waverider forebody, and the Mach number, pressure ratio and total pressure recovery coefficient at the isolator exit are 3.17, 38.9, and 0.487, respectively.