Inlet Precursor of High Velocity Inlet Based on Integral Controlled Ridge Pressure Distribution

Abstract

The invention discloses a high-speed inlet precursor based on an overall controllable ridge pressure distribution. The precursor is a bump surface with a three-dimensional ridge pressure distribution. The intersection line between the flow field and the intercepting plane determines a parabolic precursor contour line; (2) centering on the midpoint of the opening position of the precursor contour line, sweeping along the circumference of the precursor contour line to obtain a number of discrete (3) Arrange ridge-like pressure distribution curves on each two-dimensional shape line, and several ridge-like pressure distribution curves form a quasi-circumferential pressure distribution cluster; (4) Finally, based on the pressure distribution, reverse the surface to obtain The bump surface of the three-dimensional ridge-like pressure distribution of the precursor. The invention takes into account the high-efficiency displacement of the hypersonic boundary layer, the reduction of the external resistance of the precursor, and the uniformity of the flow field in the middle and rear of the bump, which is beneficial to the arrangement of the hypersonic air inlet.

Description

technical field [0001] The invention belongs to the field of aircraft precursor design, and relates to a hypersonic aircraft precursor that takes into account both low energy flow displacement and surface external resistance. Background technique [0002] The hypersonic precursor is the aerodynamic transition section between the body of the high-speed air-breathing aerospace cruiser and the air inlet. Non-uniform flow for intake air capture, etc. At the same time, the precursor is designed based on various complex configurations of the airframe, providing a more feasible geometric surface for the arrangement of the air intake. [0003] At present, research on hypersonic precursors at home and abroad is mainly based on the design of waveriders, that is, shock waves are installed on the contour of the aircraft precursor. After the tissue wave, the airflow rolls over and overflows outward, locking the compressed airflow inside the precursor shock wave, and finally achieves th...

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Problems solved by technology

[0005] Purpose of the invention: The purpose of the invention is to address the deficiencies of the prior art, to provide a high-speed inlet precursor based on the overall controllable ridge pressure distribution, to solve the two problems of improving the displacement of the boundary layer and the control of the external resistance of the profile contradictory question

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