Aerodynamic configuration of a wide-range reversible vehicle

Abstract

The design of wide-range high-efficiency aerodynamic configurations is one of the most important key technologies in the research of near-space hypersonic vehicles. A double-sided intake configuration with different inlets on the upper and lower surfaces is proposed to adapt to wide-range flight. Firstly, the double-sided intake configuration’s design method and flight profile are delineated. Secondly, Computational Fluid Dynamics (CFD) numerical simulation based on multi-Graphics Processing Unit (GPU) parallel computing is adopted to evaluate the vehicle’s performance comprehensively, aiming to verify the feasibility of the proposed scheme. This evaluation encompasses a wide-range basic aerodynamic characteristics, inlet performance, and heat flux at critical locations. The results show that the inlets of the designed integration configuration can start up across Mach number 3.5 to 8. The vehicle possesses multi-point cruising capability by flipping the fuselage. Simultaneously, a 180°rotation of the fuselage can significantly decrease the heat accumulation on the lower surface of the vehicle, particularly at the inlet lip, further decreasing the temperature gradient across the vehicle structure. This study has some engineering value for the aerodynamic configuration design of wide-range vehicles. However, further study reveals that the flow phenomena at the intersection of two inlets are complex, posing potential adverse impacts on propulsion efficiency. Therefore, it is imperative to conduct additional research to delve into this matter comprehensively.