关键词: 乘波前体, 内收缩进气道, 一体化设计, 流线追踪, 数值模拟

Abstract: In order to study the flow field and aerodynamics performance of inlet system with two inlets on each side, an inlet system for a hypersonic aircraft with a waverider forebody and hypersonic inward turning inlets with controlled pressure rise law is designed and numerically simulated, whose flow field and characteristics of speed, angle of attack and sideslip angle are obtained. The results indicate that, at the design point, the external flow filed of the forebody is independent of the inlet internal flow filed, but at take-over Mach number the leading shock waves by the forebody and the inlet are coupling. Because the boundary layer does not enter the inlets, the interaction of the shock wave and the boundary layer is weak, and so there is no separation in the flow field. With the increase of the freestream Mach number, the total pressure recovery coefficient decreases, the compression ratio increases greatly, but the lift-drag ratio almost does not change. With the increase of the angle of attack, the mass capture ratio and compression ratio increase greatly, the total pressure recovery coefficient decreases slightly, and the lift-drag ratio increases. With the increase of the sideslip angle, the overall performance of the two inlets deceases, and the inlet at downwind decreases more than the other at upwind.

Key words: waverider forebody, inward turning inlets, integrated design, streamline tracing, numerical simulation