黏性边界层修正对前体/进气道一体化乘波布局气动性能影响分析

王旭东; 王江峰; 程克明; 陈江涛

doi:10.7638/kqdlxxb-2020.0021

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黏性边界层修正对前体/进气道一体化乘波布局气动性能影响分析

研究论文 | 更新时间：2026-05-28

- 黏性边界层修正对前体/进气道一体化乘波布局气动性能影响分析
- Aerodynamic analysis of viscous boundary layer correction on integrated airframe-inlet waverider
- 空气动力学学报 2021年39卷第3期页码：62-70
- 作者机构：
  
  1. 南京航空航天大学航空宇航学院,南京,210016
  2. 中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
  
  王旭东（1990-），河南信阳人，博士，研究方向：高超声速飞行器气动布局设计. E-mail：woody.w@nuaa.edu.cn
  王江峰*（1970-），江苏南京人，教授，研究方向：高超声速气动布局设计，喷流控制，燃烧，电磁流场数值模拟等. E-mail：wangjf@nuaa.edu.cn
- 基金信息：
  
  国家数值风洞工程（ NNW）
- DOI：10.7638/kqdlxxb-2020.0021
  中图分类号： V411.8
- 纸质出版：2021
- 稿件说明：
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王旭东, 王江峰, 程克明, 等. 黏性边界层修正对前体/进气道一体化乘波布局气动性能影响分析[J]. 空气动力学学报, 2021, 39(3): 62−70.

WANG Xudong, WANG Jiangfeng, CHENG Keming, et al. Aerodynamic analysis of viscous boundary layer correction on integrated airframe-inlet waverider[J]. 2021, 39(3): 62-70.
王旭东, 王江峰, 程克明, 等. 黏性边界层修正对前体/进气道一体化乘波布局气动性能影响分析[J]. 空气动力学学报, 2021, 39(3): 62−70. DOI： 10.7638/kqdlxxb-2020.0021

WANG Xudong, WANG Jiangfeng, CHENG Keming, et al. Aerodynamic analysis of viscous boundary layer correction on integrated airframe-inlet waverider[J]. 2021, 39(3): 62-70. DOI： 10.7638/kqdlxxb-2020.0021.

摘要

针对基于流线追踪生成的乘波进气道在内流部分存在较大黏性误差的问题，以构建具有消波隔离段的内外流一体化乘波气动布局为目的，发展了一种多级波系锥导或吻切锥乘波体的边界层黏性修正方法。在基于特征线法的多级前体与截短Busemann进气道一体化乘波布局设计方法基础上，耦合了高超声速可压缩轴对称流动的冯•卡门动量方程积分方法，通过修正边界层位移厚度来提高黏性情况下与设计预期的吻合度。对修正前后的一体化乘波构型进行了设计状态下的流场对比验证以及非设计状态下给定马赫数和迎角范围下的气动性能影响分析。计算结果显示，设计状态下黏性修正构型的前体两级激波和入口反射激波位置与设计预期基本一致，消除了隔离段内多次反射激波，进气道流量比增加4.51%，出口总压损失减少8.23%；非设计状态下修正构型同样具备更强的来流捕获能力和更小的出口冲压损失。所发展的方法能够提升内外流一体化乘波布局设计方法的精度，适用于吸气式高超声速飞行器前体/进气道的精确设计。

Abstract

Waverider generated by streamline tracing has a large viscous error in the inner flow of its inlet. To design the integrated airframe-inlet waverider with no reflected shock waves in its isolator

a method of viscous boundary-layer correction has been developed in the present study for the cone-derived or osculating-cone waverider with multistage shock waves. The new approach is based on the method of characteristics (MOC) for the waverider design of multistage forebody and truncated Busemann inlet

and couples with the integration method of von Karman momentum equations for the hypersonic compressible axisymmetric flow. The displacement thickness of boundary layer is corrected to improve the consistency with the design expectation in viscous state. Numerical simulations of two waveriders before and after the viscous correction are comparatively validated under the design conditions. Meanwhile

for given Mach numbers and angles of attack

the aerodynamic performances are analyzed off the design conditions. The results show that

in the design state

the two-stage forebody shock waves and the entrance shock wave of the viscous corrected configuration are basically consistent with the design expectation that the reflected shock waves in its isolator are eliminated. The flowrate ratio of the inlet increases by 4.51%

and the total pressure loss at the outlet decreases by 8.23%. Off the design state

aerodynamic performances of the corrected waverider show the same superiority

which has stronger incoming flow capture capability and smaller total pressure loss. The developed method can increase the accuracy for the design of integrated airframe-inlet waveriders

and can also be applied to the precise design of the forebody and inlet of air breathing hypersonic vehicles.

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references

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