Integration of inward-turning inlet with airframe based on dual-waverider concept

Abstract

This paper proposes an inward-turning-inlet–forebody integration methodology based on the dual-waverider concept. For the design concept and the designed flight conditions, both the airframe and inlet benefit from the waverider's high lift-to-drag ratio and the ideal compression performance of its propulsion system. The critical issue is to construct a complex three-dimensional shock wave that accounts for both the inlet and airframe. A method is then proposed for connecting the axisymmetric flow fields of the internal and external flows. The compression surface of the integrated vehicle is then generated from the streamlines obtained with a series of axisymmetric basic flows. Finally, the integration configuration is verified using computational methods, and its viscous effects are analyzed under both on- and off-design conditions via numerical simulations. The results show that a configuration designed using the proposed approach has a high corresponding lift-to-drag ratio and high hypersonic inlet performance.