两种乘波前体/进气道一体化设计与性能研究

Integrated design and performance research of waverider forebody/inlet

建立了由激波面推算波后流场的计算方法,设计了能够产生三道封闭圆锥激波的相交锥模型.以此为基础生成了具有三道封闭激波的乘波前体和具有一道封闭激波两道平面激波的乘波前体对比模型.分别对两种乘波前体与进气道一体化模型进行了全三维流场计算,研究了两模型在不同飞行状态下的气动性能.结果表明三道封闭激波乘波前体模型相比对比模型具有较大的气动性能优势.在进气道进口截面处边界层厚度几乎相等的情况下,流量系数提高了3.4%,总压恢复系数提高了8%,进气道进口截面流场不均匀度降低了8.8%.相比低于设计马赫数和负攻角,两模型在高于设计马赫数和正攻角有较大的封闭激波飞行范围.CFD计算结果表明,对于乘波前体设计马赫数应低于实际飞行马赫数,并且宜采用正攻角飞行.

A method to compute the flow field from given shock wave was developed, and intersected cones that can generate three closed shock waves were designed. Based on the intersected cones, a waverider forebody that can generate three attached shock waves as well as a comparative reference waverider forebody that can generate one attached shock wave and two plane shock waves were designed. To better understand the performance of two forebodies, three-dimensional flow field simulation of two forebodies integrated with hypersonic inlet was conducted. The computational results show that the performance of original waverider is much better than that of comparative reference waverider. Compared with the comparative reference model, the flow coeffi- cient and the recovery coefficient of total pressure are increased by 3.4% and 8%, respectively. The distortion coefficient of inlet is decreased by 8.8 %. Two waverider forebodies integrated with hypersonic inlet show better perforemance in high mach number and positive attack angle region than that in low mach number and negative attack angle. CFD predictions show that the design mach number of waverider forebody should be less than the flight roach number, and the positive attack angle should be taken for waverider.