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Experimental investigation of the control of shock/boundary layer interaction based on dynamic vortex generator

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology Pub Date : 2025-03-31 DOI:10.1016/j.ast.2025.110175

Yue Zhang , Mingzhu Chen , Ziyun Wang , Mingchi Pang , Huijun Tan , Haicheng Zhu , Mengge Wang

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引用次数: 0

Abstract

The shock wave/boundary layer interaction (SWBLI) is an important flow characteristic in high-speed aircraft flow fields. However, the boundary layer separation caused by SWBLI will have a negative impact on the performance of the inlet. In this paper, the dynamic vortex generator (hereinbelow referred to as the dynamic VG) is designed and realized. Wind tunnel experiments are conducted to demonstrate the control capability of the array of dynamic VGs on SWBLI, while also investigating the influence of different shock impingement positions. To analyse the flow characteristics of the flow field more clearly, numerical methods are employed in this paper. Initially, the flow field in the uncontrolled case is investigated with a flow turning angle (

α

) set at 10 ° and a streamwise distance from the shock impingement position to the origin (

D_{p}

) of 25 times the maximum lift height of vortex generator (

h_{v}

). The experimental results indicate that SWBLI causes large-scale flow separation in the boundary layer. The maximum distance between separation line and reattachment line (

L_{s e p}

) is 13.8

h_{v}

, which negatively impacts the performance of hypersonic inlet. After the introduction of the array of dynamic VGs for control, the size of the separation zone decreases, confirming its effective control. This improvement is attributed to the VG-induced flow vortex pairs, which augment momentum in the near-wall region, thereby enhancing resistance to adverse pressure gradient and mitigating boundary layer separation. Moreover, the array of dynamic VGs exhibits superior flow control compared to the array of traditional VGs. This enhanced capability stems from a variable-strength pulsating vortex system generated by the dynamic VG, which diminishes the strength of the separation induced vortex in the SWBLI, thereby improving flow control effectiveness. Additionally, its unique “suction” and “extrusion” effects of the array of dynamic VGs continuously energize the airflow. At

t

= 0.5

T

, when the array of dynamic VGs reaches its maximum height, the control effect on flow separation is optimal, with an

L_{s e p}

= 11

h_{v}

, a reduction of 2.8

h_{v}

compared to the uncontrolled case. Furthermore, the study elucidated the impact of varying shock impingement positions on the control capabilities of the array of dynamic VGs. The best control effect is achieved at

D_{p}

= 22.5

h_{v}

, resulting in a 20.3 % reduction in the

L_{s e p}

of separation zone compared to the uncontrolled case.

查看原文本刊更多论文

基于动态涡发生器控制激波/边界层相互作用的实验研究

激波/边界层相互作用（SWBLI）是高速飞机流场中一个重要的流动特性。然而，由SWBLI引起的边界层分离会对进气道的性能产生负面影响。本文设计并实现了动态涡发生器（以下简称动态涡发生器）。通过风洞实验验证了动态VGs阵列对SWBLI的控制能力，同时研究了不同冲击位置对SWBLI的影响。为了更清晰地分析流场的流动特性，本文采用了数值方法。首先，研究了非受控情况下的流场，将流动转角（α）设为10°，激波撞击位置到原点的沿流距离（Dp）设为涡发生器最大升力高度（hv）的25倍。实验结果表明，SWBLI在边界层中引起了大规模的流动分离。分离线与再附着线（Lsep）之间的最大距离为13.8hv，这对高超声速进气道的性能有不利影响。引入动态VGs阵列进行控制后，分离区的大小减小，证实了其控制的有效性。这种改善归因于vg诱导的流动涡对，它增加了近壁区域的动量，从而增强了对逆压梯度的抵抗力，减轻了边界层分离。此外，与传统的VGs阵列相比，动态VGs阵列具有更好的流动控制能力。这种能力的增强源于动态涡组产生的变强度脉动涡系统，它减弱了SWBLI中分离诱导涡的强度，从而提高了流动控制效果。此外，其独特的“吸力”和“挤压”效应的阵列动态VGs不断激励气流。在t = 0.5T时，当动态VGs阵列达到最大高度时，对流动分离的控制效果最佳，Lsep = 11hv，比未控制情况降低2.8hv。此外，研究还阐明了不同冲击位置对动态VGs阵列控制能力的影响。在Dp = 22.5hv时，控制效果最佳，分离区Lsep较未控制情况降低20.3%。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Aerospace Science and Technology 工程技术-工程：宇航

CiteScore

10.30

自引率

28.60%

发文量

654

审稿时长

54 days

期刊介绍： Aerospace Science and Technology publishes articles of outstanding scientific quality. Each article is reviewed by two referees. The journal welcomes papers from a wide range of countries. This journal publishes original papers, review articles and short communications related to all fields of aerospace research, fundamental and applied, potential applications of which are clearly related to: • The design and the manufacture of aircraft, helicopters, missiles, launchers and satellites • The control of their environment • The study of various systems they are involved in, as supports or as targets. Authors are invited to submit papers on new advances in the following topics to aerospace applications: • Fluid dynamics • Energetics and propulsion • Materials and structures • Flight mechanics • Navigation, guidance and control • Acoustics • Optics • Electromagnetism and radar • Signal and image processing • Information processing • Data fusion • Decision aid • Human behaviour • Robotics and intelligent systems • Complex system engineering. Etc.