Inner channel design method of hypersonic-speed inner rotary type air inlet channel

Abstract

The invention discloses an inner channel design method of a hypersonic-speed inner rotary type air inlet channel. By appointing the shapes and positions of sections of an inlet and an outlet of an inner channel, and a three-dimensional tangential direction of each point on the sections, a series of three-dimensional smooth curves from the inlet of the inner channel to the section of a throat channel are constructed, so that the smooth transition from the section of the inlet of the inner channel to the section of the outlet of the inner channel is realized. By changing relative positions of control points in transition curves, concave and convex properties of a molded line keep consistent; meanwhile, a slope change rule of the transition molded line also can be controlled, so that relative positions of lip cover reflection shock waves and shoulder expansion fans of the rotary type air inlet channel are changed, and a lip cover reflection shock wave / boundary layer interference phenomenon is properly controlled. The method has no limitation on the shapes and directions of the sections of the inlet and the outlet of the inner channel, and a complicated transformation process of the shapes of the inlet and the outlet does need to be considered, and a molded surface coherent phenomenon does not occur; and a flow capturing property of the air inlet channel is not influenced so that the inner channel design method has relatively good commonality.

Description

technical field [0001] The invention relates to the field of aircraft air intake design, in particular to an inner channel design method of a hypersonic inward turning air intake. Background technique [0002] The hypersonic inward turning inlet is a new inlet configuration designed by streamline tracing method. At the design point state, the shock wave of the precursor is close to the mouth, realizing full flow capture, avoiding the three-dimensional span overflow of the traditional binary inlet, and the three sides of the precursor compression surface of the internal rotation inlet participate in the compression, and the compression efficiency It is taller and can achieve short-distance and large diffusion; not only that, the precursor of the inward-turning inlet is easy to integrate with the aircraft fuselage, so it has won the favor of researchers and has become the next-generation hypersonic plan in the United States. air intake plan. [0003] Since the concept of the...

AI Technical Summary

Problems solved by technology

In recent years, Nanjing University of Aeronautics and Astronautics has developed a general diffuser design method (patent publication number: CN103950544A), because the prerequisite for this method is that all points on the inlet and outlet sections must meet the tangential direction level, and for internal rotation The front body of the air inlet presents a highly three-dimensional shrinkage state, and the tangent direction of each point on the inlet section is different, and this design method is no longer applicable

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