Flow-field characteristics analyses on shock-wave/boundary-layer interaction of TSTO parallel separation

FAN Xiaohua; ZHANG Qinghu; LUO Lei; LIN Jingzhou; TANG Zhigong

doi:10.7638/kqdlxxb-2022.0184

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Flow-field characteristics analyses on shock-wave/boundary-layer interaction of TSTO parallel separation

更新时间：2026-05-28

- Flow-field characteristics analyses on shock-wave/boundary-layer interaction of TSTO parallel separation
- Vol. 41, Issue 5, Pages: 87-97(2023)
- 作者机构：
  
  1. 中国空气动力研究与发展中心超高速空气动力研究所,绵阳,621000
  2. 中国空气动力研究与发展中心计算空气动力研究所,绵阳,621000
  3. 中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0184
  CLC： V211;V411
- Published：2023
- 稿件说明：
移动端阅览
范孝华, 张庆虎, 罗磊, 等. TSTO并联分离激波/边界层干扰流动特性分析[J]. 空气动力学学报, 2023, 41(5): 87−97.

FAN Xiaohua, ZHANG Qinghu, LUO Lei, et al. Flow-field characteristics analyses on shock-wave/boundary-layer interaction of TSTO parallel separation[J]. 2023, 41(5): 87-97.
范孝华, 张庆虎, 罗磊, 等. TSTO并联分离激波/边界层干扰流动特性分析[J]. 空气动力学学报, 2023, 41(5): 87−97. DOI： 10.7638/kqdlxxb-2022.0184

FAN Xiaohua, ZHANG Qinghu, LUO Lei, et al. Flow-field characteristics analyses on shock-wave/boundary-layer interaction of TSTO parallel separation[J]. 2023, 41(5): 87-97. DOI： 10.7638/kqdlxxb-2022.0184.

摘要

针对两级入轨飞行器的缩比模型，通过试验与数值模拟相结合的方式，在马赫数6条件下开展典型级间距状态的激波/边界层干扰流场研究，详细分析干扰区壁面及空间的流动结构与特性。结果表明：试验中模型壁面边界层在激波入射之前为层流状态，在强激波干扰后迅速转捩为湍流状态，因此试验结果在第一道激波作用结束之前与层流计算结果吻合，而在第一道激波作用结束之后与湍流计算结果一致；激波/边界层干扰呈现复杂的三维流动特征和明显的开放结构，强激波在壁面形成的高压区呈弧状向下游展开，轨道级头部产生的入射激波在级间来回反射，强度依次递减；同时，干扰区内存在展向弯曲的主分离线与再附线、沿流向排列的二次分离线与再附线、流动剪切形成的旋涡结构以及包括鞍点、结点、焦点在内的临界点；层流边界层受到激波作用形成的分离区明显大于湍流边界层，同时开放特征更为显著。

Abstract

Through the combination of wind-tunnel tests and numerical simulations

the shock-wave/boundary-layer interaction (SWBLI) of interstage flow fields within typical stage clearances of a Two-Stage-To-Orbit (TSTO) scaled model at Mach number 6 is studied. Flow fields in the interference areas are analyzed in detail. Results show that the impingement of shock waves induces the boundary layers to transit rapidly to turbulent states

which numerical simulations have accurately captured. SWBLI induces complex three-dimensional flow characteristics with prominent open features. The high wall pressure induced by the strong shock wave spreads downstream in an arc. The incident shock wave generated by the orbiter head constantly reflects between the two stages and gradually weakens. Meanwhile

the spanwise curved principal separation and reattachment lines

streamwise aligned secondary separation and reattachment lines

and critical points

including saddle

node

focus

and vortical structure induced by shear layers

are also observed in the interference areas. The shock wave impingement induces a larger separation area and more obvious open features in the laminar state than in the turbulent state.

关键词

Keywords

references

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