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A Design Method for Hypersonic Inlet

A design method and hypersonic technology, which is applied to the intake port of the turbine/propulsion device, calculation, combustion air/combustion-air treatment, etc., can solve the problem of large total pressure recovery coefficient of the intake port, and achieve total pressure recovery The effect of large coefficient

Active Publication Date: 2019-09-03
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] Aiming at the problem that the traditional inlet design needs to pre-set the internal flow field and it is difficult to maximize the total pressure recovery coefficient of the inlet while satisfying the shock wave seal, the present invention proposes a hypersonic inlet design method

Method used

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  • A Design Method for Hypersonic Inlet
  • A Design Method for Hypersonic Inlet
  • A Design Method for Hypersonic Inlet

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Experimental program
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Effect test

Embodiment

[0061] Embodiments of the present invention include the following steps:

[0062] S1, using the functional relationship to generate the reference flow field profile of the inlet, mainly including:

[0063] S101, according to the geometric constraints of the inlet structure design, determine the vertex of the reference flow field surface, the specific method is:

[0064] (1) According to the center body radius rc=0.1, determine the B coordinate (0,0.1) of the lower apex of the inlet inlet, and set the length of OC as unit 1, and determine the coordinate of point C (0,1);

[0065] (2) According to the lip distance from the inlet length Lo = 3.6, determine the inlet lip apex D (3.6, 0.1);

[0066] (3) According to the total length of the inlet channel Lt=5, and the eccentricity between the inlet and outlet is 0.3, determine the outlet center point Oo(5,0.25).

[0067] S102, according to the geometric constraints of the inlet structure design, determine the end point E of the ou...

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Abstract

The invention relates to a design method of a hypersonic velocity air inlet channel. The design method comprises the steps of creating a reference flow field profile based on a functional relation; optimally designing axial symmetric reference flow fields of the air inlet channel; and then obtaining a three-dimensional profile of the air inlet channel through a streamline tracking method. Comparedwith the prior art, the method has the advantage that the problem that the design of a traditional air inlet channel is performed by designing inner flow field condition firstly, and the total pressure recovery coefficients of the air inlet channel cannot reach the maximum value while the shock wave sealing of a port is realized, can be solved.

Description

technical field [0001] The invention belongs to the technical field of hypersonic propulsion, and relates to a design method of a scramjet intake port, in particular to a design method of a hypersonic inner steering intake port. Background technique [0002] The scramjet engine is mainly composed of four parts: the intake port, the isolation section, the combustion chamber and the tail nozzle. The hypersonic inlet is the air supply part of the scramjet engine, which provides sufficient and high-quality incoming flow for the engine combustion chamber to ensure the normal and efficient operation of the engine. Its performance directly affects the thrust of the engine and even the effective operation of the entire aircraft. [0003] The hypersonic inward turning inlet is based on the axisymmetric inward turning reference flow field, and the inlet is obtained by streamline tracing technology. It is characterized by the flow in the inlet being compressed by shock waves and Mach w...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/04G06F17/50
CPCF02C7/04G06F30/17
Inventor 熊冰范晓樯王翼陶渊蒙泽威
Owner NAT UNIV OF DEFENSE TECH
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