The Integration Methodology For Hypersonic Internal&External Flow Basis Of The Dual Waverider Concept

Based on the integrated method of the airframe and hypersonic inlet existed,a new concept about integration of hypersonic external and internal flow based on dual waverider theory is proposed.The main research jobs includes:(1)Various waverider design methods and its applications in the airframe-inlet integration are summarized and classified.(2)The detailed investigation of the waverider application in the external and internal flow components is carried out,and with the osculating waverider,a dual waverider theory which can satisfy the requirement of aerodynamic and geometrical continuous morphing between external and internal flow is developed.The comparison between the external and internal flow is investigated,and the control method for the flowfield compression mode by changing the radius of the flowfield is proposed.(3)The dual waverider method for matching waverider are proposed,which avoided the interaction between the external and internal components.(4)An integration concept which can satisfy the preassigned pressure distribution is proposed.The concept control the wall pressure distribution of external and internal components simultaneously by inverse designing compression surface.(5)The integration method for matching conical body is proposed.Considering the constraint of the slenderness ratio,the integration method adopted the concept between upstream and downstream.(6)Finally,the high enthalpy tunnel tests of the conical body and inlet integration configuration is studied.The results show that,under the conical body condition,the entrance of inlet should be inward turning to increase the compression effect,after meeting the mass flow requirement of downstream components.It is hopeful that the current work is able to provide new technical reserves for the airbreathing high-speed vehicle design in the furture.