转捩位置对尖锥静/动气动特性影响的数值模拟

王新光; 陈琦; 张毅锋; 何琨; 万钊

doi:10.7638/kqdlxxb-2024.0067

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转捩位置对尖锥静/动气动特性影响的数值模拟

研究论文 | 更新时间：2026-05-28

- 转捩位置对尖锥静/动气动特性影响的数值模拟
- Numerical simulation of the effect of transition position on static and dynamic aerodynamic characteristics of cones
- 空气动力学学报 2025年43卷第9期页码：1-9
- 作者机构：
  
  1. 中国空气动力研究与发展中心,绵阳,621000
  2. 空天飞行空气动力科学与技术全国重点实验室,绵阳,621010
- 作者简介：
  
  王新光（1985—），男，内蒙古呼和浩特人，高级工程师，研究方向：高速复杂流动数值模拟. E-mail：xinguangwang2014@126.com
  张毅锋*，研究员，研究方向：高速流动边界层转捩. E-mail：zyf63867@163.com
- 基金信息：
  
  省部级高层次科技创新人才工程
- DOI：10.7638/kqdlxxb-2024.0067
  中图分类号： V211.7;O35
- 纸质出版：2025
- 稿件说明：
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王新光, 陈琦, 张毅锋, 等. 转捩位置对尖锥静/动气动特性影响的数值模拟[J]. 空气动力学学报, 2025, 43(9): 1−9.

Wang Xinguang, CHEN Qi, ZHANG Yifeng, et al. Numerical simulation of the effect of transition position on static and dynamic aerodynamic characteristics of cones[J]. 2025, 43(9): 1-9.
王新光, 陈琦, 张毅锋, 等. 转捩位置对尖锥静/动气动特性影响的数值模拟[J]. 空气动力学学报, 2025, 43(9): 1−9. DOI： 10.7638/kqdlxxb-2024.0067

Wang Xinguang, CHEN Qi, ZHANG Yifeng, et al. Numerical simulation of the effect of transition position on static and dynamic aerodynamic characteristics of cones[J]. 2025, 43(9): 1-9. DOI： 10.7638/kqdlxxb-2024.0067.

摘要

高速再入飞行器在进入临近空间时，随着雷诺数的增大会发生边界层转捩，改变飞行器的物面压力和摩阻分布，进而影响气动特性和操稳特性。轴对称飞行器由于迎风面和背风面的转捩发生位置不同形成的非对称转捩会产生诱导力和力矩，从而影响飞行器的静/动稳定性。本文基于高速数值模拟软件分析转捩对尖锥的静/动稳定性影响规律，通过给定圆锥壁面转捩位置，在其法向扩展构造出转捩控制面，实现了不同形状和位置的强制转捩模拟，强迫俯仰振动下的非定常流场数值模拟和分析结果表明：非对称转捩阵面会影响尖锥气动力/力矩的变化，随着转捩阵面后移，俯仰静稳定性降低，而动稳定性增强；边界层转捩诱导出压力和摩阻增量，在总附加力矩动导数中压力分量占主导。

Abstract

When a high-speed reentry vehicle enters the near space

the boundary layer undergoes the transition process as the Reynolds number increases. The boundary layer transition modifies the surface pressure and skin friction distributions on high-speed vehicles

thus affecting the aerodynamic and stability characteristics. The asymmetric transition fronts on inclined axisymmetric vehicles induce extra force and moment

thereby affecting the vehicle's static and dynamic stability. Consequently

an investigation into the effects of boundary layer transition on aircraft's stability is critical for the design and control of high-speed vehicles. This paper analyzed the influence of boundary layer transition on the static and dynamic stability of a sharp cone using a high-speed numerical simulation software. This was accomplished by numerical simulations of forced transition with different types of transition fronts by integrating RANS models and the forced pitching oscillation method. For this dynamic numerical simulation

a transition control surface was essential

constructed by extending the transition front from the cone surface in the wall-normal direction. Results showed that as the transition front moves backward

the static stability decreased while the dynamic stability increased. The boundary layer transition introduced additional pressure and skin friction

with the former being the primary contributor to the overall induced pitching moment dynamic derivative.

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references

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