全流面乘波前体进气道设计方法

吴颖川; 贺元元; 卫锋; 余安远

doi:10.7638/kqdlxxb-2021.0144

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全流面乘波前体进气道设计方法

专栏——内外流一体化技术 | 更新时间：2026-05-28

- 全流面乘波前体进气道设计方法
- Design of continuous streamline tracing waverider forebody inlet
- 空气动力学学报 2022年40卷第1期页码：114-118
- 作者机构：
  
  中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室,绵阳,621000
- 作者简介：
  
  吴颖川（1967-），男，四川广汉人，研究员，研究方向：高超声速空气动力学. E-mail：wyclwx2007@126.com
  贺元元*（1973-），女，上海人，研究员，研究方向：高超声速空气动力学. E-mail：hyy63713@126.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0144
  中图分类号： V211.48;V411.4
- 纸质出版：2022
- 稿件说明：
移动端阅览
吴颖川, 贺元元, 卫锋, 等. 全流面乘波前体进气道设计方法[J]. 空气动力学学报, 2022, 40(1): 114−118.

WU Yingchuan, HE Yuanyuan, WEI Feng, et al. Design of continuous streamline tracing waverider forebody inlet[J]. 2022, 40(1): 114-118.
吴颖川, 贺元元, 卫锋, 等. 全流面乘波前体进气道设计方法[J]. 空气动力学学报, 2022, 40(1): 114−118. DOI： 10.7638/kqdlxxb-2021.0144

WU Yingchuan, HE Yuanyuan, WEI Feng, et al. Design of continuous streamline tracing waverider forebody inlet[J]. 2022, 40(1): 114-118. DOI： 10.7638/kqdlxxb-2021.0144.

摘要

基于流线追踪的飞行器乘波前体设计和发动机进气道设计已有大量的研究工作，但是高超声速飞行器前体与超燃冲压发动机进气道的一体化设计一直是个难点。为了提高前体进气道整体的总压恢复和流量捕获性能，在前期飞行器乘波前体设计和进气道压缩面流线追踪设计方法的基础上，将整个基准流场分为激波压缩流场和等熵压缩流场，顺序组合，从前体激波、外压缩面到进气道内压缩面、反射激波直到喉道进行无缝连续地流线追踪，实现了全流面乘波前体进气道设计。横向三维曲面生成采用类似密切方法进行控制以实现全流面设计；纵向基准流场的构建由交叉推进特征线方法生成的激波压缩流场和反向Prandtl-Meyer流动生成的等熵压缩流场组合而成，只需输入前缘激波形状与进气道喉道出口约束；所有的控制曲线采用一种四次样条曲线进行描述。这是一种统一的基于内、外锥基准流场的前体进气道设计方法，其主要优点是具有较高的流量系数和总压恢复系数，可广泛用于高超声速飞行器前体进气道内外流一体化设计。

Abstract

A large amount of research work has been conducted on the design of high speed waveriders and engine inlets based on the streamline tracking method

but the integrated design of the forebody of hypersonic vehicles and the scramjet inlet has always been difficult. In order to improve the total pressure recovery and flow capture performance of the integrated forebody and inlet of hypersonic vehicles

the entire base flowfield is divided into a shock compression and an isentropic compression in sequence based on the methods of previous waverider forebody design and inlet compression surface streamline tracing

and a completely continuous streamline tracing is achieved connecting the forebody shockwave

the outer compression surface

the inner compression surface of the inlet

the reflection shockwaves and the inlet throat. The generation of the three-dimensional spanwise surface is controlled by a osculating method

which realizes the design of continuous stream surface. The longitudinal base flowfield is constructed by combining the shock compression flowfield generated by the cross-marching characteristic method with the isentropic compression flowfield generated by the reversed Prandtl-Meyer flow

which only requires constrains of the forebody shockwave shape and the inlet throat. All control lines are described by a kind of quartic spline curve. This is a unified method for the integrated forebody and inlet design of hypersonic vehicles based on reference flowfields of the internal and external cones. Its main advantages are that it has relatively higher flow capture and total pressure recovery coefficients and can be widely used in the integrated design of internal and external flow of hypersonic vehicles.

关键词

Keywords

references

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