Research Of A Novel Integrated Design Methodology For Inward Turning Inlet And Waverider

In this paper,the integrated design of the hypersonic inward turning inlet and the waverider is considered.Based on the method of characteristic and streamline tracing,the design of the inward turning basic flow field and the inlet are carried out by means of basic theoretical analysis and numerical simulation.In order to reduce the interaction of the internal and external flow fields between the inlet and the body,the integrated design of the inlet and waverider is carried out from the perspective of geometric splicing and the coupling of the internal and external flow fields.First of all,the research on the design method and configuration of the air breathing vehicle,the inward turning inlet and the integrated design method in hypersonic field is carried out.The general situation of the development of the air breathing hypersonic vehicle,the research status of the inward turning inlet and the integrated design method at home and abroad are summarized.And the classification of these is described in detail.The process of constructing the basic flow field is based on the theory of the rotating characteristics.The typical unit processes in the theory of the rotating characteristic are introduced,which are the interior point unit process,the direct wall point unit process,the preset wall point unit process and the shock boundary point unit process.In the process of solving the streamline,the streamline tracking method is used,which is based on the right-running Mach lines to carry out the prediction correction iterative algorithm to solve the position coordinates and flow parameters of the streamline points.The design method of inward turning inlet is based on the generating body.Under the condition of hypersonic flow,the axisymmetric basic flow field is constructed by using the theory of rotating characteristics,which is divided into four parts-the dependent region of leading shock wave,the isentropic principal compression region,the dependent region of lip shock wave,the stability region.A series of typical unit processes are used in the design and solution steps of each part.In the flow field,the projection profile of the leading edge of the inlet is designed on the base plane,and different shapes of the inward turning inlet are generated for the different projection profiles using the streamline tracing method.Finally,the numerical simulation of a circular inlet is carried out,and the results verify the correctness and validity of the design method of the basic flow field and inlet.In view of the integrated design of the inward turning inlet and the waverider,this paper studies from two ways: geometry fusion and flow field intersection.In order to increase the air intake and capture efficiency of the inlet,from the perspective of geometric fusion,the two integrated design methods are proposed-waverider / inward turning inlet and three parallel inward turning inlets.According to the proposed method,the integrated configuration is generated and simulated.In the way of flow field intersection,from the point of view of the coupling of internal and external flow fields,the integrated design method of head intake and two side intake inward turning inlet /Von Karman waverider are proposed.similarly,the configuration is generated and the numerical simulation results show that the integrated design method is correct and effective.