Design method for three-dimensional internal rotary inlet based on complete flow direction suction

Abstract

The invention discloses a design method for a three-dimensional internal rotary inlet based on complete flow direction suction, and relates to inlet boundary layer suction. The method comprises the following steps of solving an axial symmetric basic flow field by adopting a characteristic line method according to design requirements; generating a three-dimensional internal rotary inlet compression profile by applying a streamline tracing method; calculating displacement thicknesses of conical sections of different positions of the shoulder of the three-dimensional internal rotary inlet according to a displacement thickness formula; designing a complete flow direction suction opening based on the inlet compression profile and the displacement thicknesses; constructing a new inlet exit shape by the complete flow direction suction opening, and performing unidiameter backward stretching to obtain a three-dimensional internal rotary inlet separation section; and obtaining the three-dimensional internal rotary inlet which is capable of eliminating low-speed and low-energy airflow of a boundary layer completely in a flow direction and does not influence flowing characteristics of high-speed and high-energy airflow in the inlet. The self-opening performance of the three-dimensional internal rotary inlet can be remarkably improved. The low-energy flow of the boundary layer can be completely eliminated and the flowing characteristics in the inlet are not influenced.

Description

technical field [0001] The invention relates to inlet boundary layer suction, in particular to a three-dimensional inward turning inlet design method for complete flow direction suction. Background technique [0002] The development of near-space vehicles involves national security and peaceful use of space, and is one of the focuses of the current international competition for space technology. World powers represented by the United States and Russia are vigorously promoting their own hypersonic flight development programs. The scramjet engine, as the key technology for the realization of hypersonic aircraft, is one of the hot fields that countries around the world are vying to pay attention to. For a scramjet engine, a high-performance intake port is the key to designing a high-performance scramjet engine. The air inlet is located at the forefront of the hypersonic vehicle propulsion system, directly connected to the hypersonic vehicle precursor, and plays the role of co...

AI Technical Summary

Problems solved by technology

[0005] However, whether it is a forward suction tank or a reverse suction tank, there is a significant problem: the additional suction shock wave will be introduced, which will reduce the total pressure recovery; the additional shock wave and the reflected shock wave will interfere with each other, forming a complex wave system structure, it will also reduce the uniformity of the outlet, and even cause the separation of the boundary layer, and introduce new non-starting factors

Images