Design method of three-dimensional inward turning air inlet channel capable of simultaneously controlling shock wave and pressure distribution

Abstract

The invention relates to a three-dimensional inward turning air inlet channel design method capable of controlling shock wave and pressure distribution at the same time. The method comprises the following steps:(1) incoming flow conditions and incident shock wave curves are designed, and wall surface molded lines are reversely solved according to a characteristic line method; (2) extracting pressure distribution of the wall surface molded line obtained in the step (1), and designing downstream pressure distribution; (3) according to the pressure distribution obtained in the step (2), reverselysolving a wall surface molded line by utilizing a characteristic line method; (4) taking the three-dimensional revolution of the wall surface molded line obtained in the step (3) as a bus of a basicflow field, and solving the whole flow field; (5) designing a three-dimensional inward turning air inlet passage inlet in polar coordinates, and performing streamline tracking in the basic flow fieldobtained in the step (4) to obtain a three-dimensional inward turning air inlet passage compression profile; and (6) the three-dimensional inward-turning air inlet channel compression molded surface obtained in the step (5) is stretched in the equal-straight-direction backward direction to obtain an isolation section. The advantages of the three-dimensional inward turning air inlet channel are kept, meanwhile, the incident shock wave and wave back isentropic compression process is designed, and therefore a new degree of freedom is introduced for design of the three-dimensional inward turning air inlet channel.

Description

technical field [0001] The invention relates to the technical field of three-dimensional inward turning inlet design, in particular to a design method for a three-dimensional inward turning inlet with simultaneously controllable shock waves and pressure distribution. Background technique [0002] The research and development and trial production of hypersonic vehicles is one of the focuses of space technology research, and it is the technological commanding heights that all aviation powers are vying to occupy. To achieve hypersonic flight, the first technical problem to be solved is scramjet technology. The intake duct is located at the front end of the scramjet as a compressed air component, which will provide as much high-energy airflow as possible for the downstream. Therefore, scholars at home and abroad have proposed a series of design methods for the compression form of the inlet, mainly including: binary inlet, axisymmetric inlet, and side pressure inlet, and have ca...

AI Technical Summary

Problems solved by technology

However, in the existing three-dimensional internal turning inlet design process, the two factors are usually considered separately, and it is impossible to realize the simultaneous controllability of the incident shock wave and the isentropic compression process.

Images