Inverse Design of Axisymmetric Basic Flow Field on Basis of Specified Wall Aerodynamic Parameters

Abstract

With the further study of hypersonic propulsion technology, the intake system adapting to the overall demands of different aerocraft has also made great progress. In recent years, in addition to the conventional two dimensional plane compression inlet, axisymmetric inlet and sidewall compression inlet, the inward turning inlet with Busemann inlet as the external early representation has been attracting more and more attention of all countries due to its special performance. The key to form this type of inward turning inlet is the “basic flow field”, and the compression performance of the basic flow field determines the overall performance of the inward turning inlet to a large extent. In addition to the conventional axisymmetric basic flow field in Busemann form, there are generation methods of the basic flow field in many forms, but basically they are not free from the forward design approach starting from the geometric modeling. In this chapter, we focus on this key problem, make full use of the advantages of the compression flow field of curved shock wave and the second class inverse design idea proposed in this book, and design the compression surface of this kind of axisymmetric basic flow field starting from the pneumatic parameter distribution of the molded surface. For example, given the rising pressure rule of the compression surface or given the decelerating law to determine the geometric modeling of the molded surface, the high performance wall arc tangent pressurizing law and the wall arc tangent decelerating law are introduced in this book to design the process and design details of the axisymmetric basic flow field.