Design And Research On Aerodynamic Characteristic Of Two-Dimensional Adjustable Inlet's Forebody

In this paper,the numerical simulation method is used to study the aerodynamic characteristics of the forebody of a two-dimensional adjustable inlet and to design the aerodynamic configuration scheme.The different aerodynamic shapes and geometric parameters of the first and second wedges of the external compression section of the inlet are mainly studied.The effects of different geometric parameters on the aerodynamic performance of the inlet under several aerodynamic configurations are obtained.A set of geometric parameters are determined to obtain several optimal aerodynamic configurations.The performance of different aerodynamic configurations on wide-speed range is carried out by numerical simulation,and the aerodynamic performances of inlet are obtained.Firstly,the two-dimensional profile of the adjustable inlet meeting the design state is obtaind,and its three-dimensional configuration is obtained based on the two-dimensional profile.The aerodynamic performance of the vertical side-plate inlet is studied.Because there is no side-plate in the external pressure section of the three-dimensional configuration,the factors affecting the boundary layer of the inlet cause the inlet to not start.These reasons for the unstarting are studied,and different optimization schemes are designed.In order to solve the unstarting of inlet,adjusting the area of suction,changing the radius of circle at the shoulder of the inlet,moving the shoulder of the inlet and adjusting the angle of the lip,the scheme of moving the shoulder is selected.Secondly,according to the scheme obtained above,different geometric parameters of the waverider are studied by adding the waverider to the outward side of the first compression plane and keeping the second compression plane unchanged.The main parameters are the width ratio w1/w0,the parameter about angle of the forebody of the upper surface ?,the parameter about upper surface of forebody n,the parameter about lower surface of forebody m,and the parameter about curvature k on the surface of forebody.The first aerodynamic configuration scheme is that the first compression surface of the inlet is a wave multiplier and the second compression surface is a wedge.The influence of shape parameters of the first compression surface such as width ratio w1/w0,angle of forebody ? and leading edge profile control parameter n on the aerodynamic performance of the inlet is studied.The second aerodynamic configuration scheme is that the first and second compression surfaces of the inlet extend along two-dimensional symmetrical surfaces.The compression surface obtained by stretching is a two-dimensional surface and a wedge-shaped forebody.The influence of the width ratio of the forebody w1/w0 and the control parameter m of the profile under the forebody on the aerodynamic performance of the inlet is mainly studied.The third aerodynamic configuration scheme is that the first compression surface of the inlet is stretched along the stretch direction with the profile of the two-dimensional symmetrical plane,and the second compression surface is a surface with the angle of forebody as the parameter.The fourth aerodynamic configuration scheme is based on the third scheme,which mainly studies the influence of the parameter k about the first compression surface on the aerodynamic performance of the inlet.Finally,the effects of the geometric parameters of the forebody on the aerodynamic performance of the inlet under the different aerodynamic configuration schemes are obtained.According to the influence rules obtained and the performance of various aspects,a set of geometric parameters of the forebody is preliminarily determined,so that the aerodynamic configuration schemes corresponding to the parameters combination have better overall performance of the inlet can be designed.At the same time,Aerodynamic characteristics of the forebody/inlet in the wide speed range of four schemes are obtained.