基于改进的<i>k-ω-γ</i>转捩模式预测高超声速飞行器气动特性

王亮; 周玲

doi:10.7638/kqdlxxb-2019.0146

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基于改进的k-ω-γ转捩模式预测高超声速飞行器气动特性

研究论文 | 更新时间：2026-05-28

- 基于改进的k-ω-γ转捩模式预测高超声速飞行器气动特性
- Prediction of aerodynamic characteristics of hypersonic vehicle by improved k-ω-γ transition model
- 空气动力学学报 2021年39卷第3期页码：51-61
- 作者机构：
  
  1. 水利部农村电气化研究所,杭州,310012
  2. 北京理工大学,北京,100081
- 作者简介：
  
  王亮（1992-），男，硕士，工程师，研究方向：空气动力学. E-mail：lwang@hrcshp.org
  周玲*，女，博士，副研究员，研究方向：边界层转捩. E-mail：lingzhou@bit.edu.cn
- 基金信息：
  
  国家自然科学基金青年科学基金（11702104）;中央级公益性科研院所基本科研业务费专项资金（Y118006，Y919020）
- DOI：10.7638/kqdlxxb-2019.0146
  中图分类号： V411.4
- 纸质出版：2021
- 稿件说明：
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王亮, 周玲. 基于改进的k-ω-γ转捩模式预测高超声速飞行器气动特性[J]. 空气动力学学报, 2021, 39(3): 51−61.

WANG Liang, ZHOU Ling. Prediction of aerodynamic characteristics of hypersonic vehicle by improved k-ω-γ transition model[J]. 2021, 39(3): 51-61. DOI: 10.7638/kqdlxxb-2019.0146.
王亮, 周玲. 基于改进的k-ω-γ转捩模式预测高超声速飞行器气动特性[J]. 空气动力学学报, 2021, 39(3): 51−61. DOI： 10.7638/kqdlxxb-2019.0146

WANG Liang, ZHOU Ling. Prediction of aerodynamic characteristics of hypersonic vehicle by improved k-ω-γ transition model[J]. 2021, 39(3): 51-61. DOI: 10.7638/kqdlxxb-2019.0146. DOI：

摘要

为验证边界层转捩对高超声速飞行器气动特性的影响，采用改进的

k-ω-γ

转捩模式对类X-51A高超声速飞行器进行了全机边界层转捩预测。不仅系统分析了飞行攻角和雷诺数对边界层转捩的影响规律，同时研究了边界层转捩对飞行器气动力和进气道性能的影响。发现边界层转捩对飞行器升力系数和俯仰力矩系数影响较小，对阻力系数影响较大。针对本文算例，全层流计算较转捩计算预测的阻力系数偏低可达20%～30%。此外，边界层转捩可减小高超声速飞行器前体压缩面拐角处的分离，降低喉道截面马赫数、提高增压比。以上研究结果可为高超声速飞行器的控制系统和推进系统设计提供技术参考，显示了改进的

k-ω-γ

转捩模式具有较大的工程应用潜力。

Abstract

In order to verify the influence of boundary layer transition on the aerodynamic characteristics of hypersonic vehicles

an improved

k-ω-γ

transition model was used to predict the boundary layer transition of the X-51A-like hypersonic vehicle. This study not only analyzed the effects of angle of attack and Reynolds number on the boundary layer transition

but also studied the effects of boundary layer transition on the aerodynamics and the inlet performance of the vehicle. It is found that boundary layer transition has little influence on the lift coefficient and pitching moment coefficient of the vehicle

but has a great effect on the drag coefficient. F

or the case studied

the drag coefficient predicted by the full laminar flow simulation is 20%～30% lower than that by the transition model. In addition

boundary layer transition can reduce the separation at the corner of the compression surface of the hypersonic vehicle forebody

decrease the Mach number of the throat section

and increase the pressure ratio. Current research results provide a technical reference for the design of control and propulsion systems of hypersonic vehicles

and show that the improved

k-ω-γ

transition mode has great potential in engineering applications.

关键词

Keywords

references

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基于改进的k-ω-γ转捩模式预测高超声速飞行器气动特性

Prediction of aerodynamic characteristics of hypersonic vehicle by improved k-ω-γ transition model

DOI：10.7638/kqdlxxb-2019.0146

摘要

Abstract

关键词

Keywords

references