Design method of compression surface-biased fixed-geometry high-speed air inlet channel inlet section

Abstract

The invention discloses a method for designing an inlet section of a fixed-geometry high-speed air inlet channel with an offset compression surface. The method comprises the steps of designing a waverider forebody and designing an air inlet channel, wherein the design of the waverider forebody is combined with an aircraft shape and an internal load condition, the outline of the waverider forebodyand the shock wave shape of the waverider forebody are set, and a cone-like three-dimensional curved surface shock wave is emitted by the aircraft forebody, and the design of the air inlet channel isthat the air inlet channel is determined to be of a double-air-inlet-channel structure on the basis of the outline of the waverider forebody, the shock waves emitted by the waverider forebody and theboundary layer displacement effect of all cross sections along the way, an air inlet channel lip captures incoming flow after the shock waves of the forebody, overflow windows are arranged on the twosides of the double-air-inlet-channel structure, and overflow capacity is improved. Through a flow field organization scheme of double-outer-side overflow, the integrated design of the hypersonic airinlet channel and the precursor is assisted, and the overflow amount can be correspondingly changed along with the change of Mach number.

Description

technical field [0001] The invention belongs to the field of hypersonic aircraft precursor / integrated aerodynamic design, and in particular relates to a structural design of an inlet section of a high-speed air inlet. Background technique [0002] The hypersonic precursor is the aerodynamic transition section between the body and the inlet of the high-speed air-breathing aerospace cruiser. Uniform flow for intake air capture etc. At the same time, the precursor is designed based on various complex configurations of the airframe, providing an aerodynamic profile with high feasibility for integrated matching for the layout of the air inlet. [0003] At present, in order to achieve high-efficiency and long-range aerospace flight at home and abroad, the air intake system needs to have the following characteristics: 1) High-efficiency low-energy flow displacement capability. Low-energy flow is an unavoidable problem in the design of a hypersonic air intake system. Trying to dis...

AI Technical Summary

Problems solved by technology

[0005] Purpose of the invention: The purpose of the present invention is to address the deficiencies in the prior art, and provide a design method for the inlet section of the fixed-geometry high-speed inlet with offset compression surface, so that the overflow volume can be adaptively changed with the change of the flight state, and solve the problem of low Mach The flow in front of the throat is too large for a few hours, resulting in flow blockage, and even the problem that the intake port does not start

Images