Aerodynamic Layout Design Method Of The Waverider Forebody/Inlet Configuration

This paper mainly focus on the aerodynamic layout design method of waverider forebody/inletIntegrated configuration. Specific work includes the following aspects:First, a method based on the combination of wedge/cone flow field to generate waverider iselaborated in detail by using three different wedge/cone flow field to generate three differentwaverider configurations. numerical simulation verification and analysis is conducted on the threewaveriders.Second, four plane oblique shock flow field is introduced to generate hypersonic inlet. By usingstreamline tracing method, three hypersonic inlets were obtained according to the size of the outletsection of the inlets. Numerical computation and performance comparison is conducted on the threehypersonic inlet.Then, integrated design of waverider forebody/inlet is carried out based on waverider and inletdiscussed above. Two Integrated configurations of hypersonic vehicle are designed in accordance withthe design requirements. In addition, the up surface of aircraft was designed as free expansion, withthe simplify processing of scramjet isolator, combustor, nozzle and other components.Finally, the aerodynamic interface division of hypersonic vehicle was analyzed. CFD software isused to simulate the integration of Internal and external flow of two aircraft configuration on multipleconditions, analysis and comparison of the overall aerodynamic characteristics of the two hypersonicvehicles is investigated.