Article
Mechanics
Zhigang Zhang, Fulin Tong, Junyi Duan, Xinliang Li
Summary: This study conducted a direct numerical simulation of an incident shock wave impinging on a 12° supersonic turbulent expansion corner at a 33.2° angle, revealing the significant influence of expansion on the physics of interaction. The expansion led to reduced wall pressure and separation bubble size, affecting the motion induced by the shock. The study also analyzed the evolution of the reattached boundary layer and the generation mechanism of skin friction.
Article
Engineering, Aerospace
Andreas Gross, Jesse Little, Hermann F. Fasel
Summary: This study investigates turbulent shock-wave boundary layer interactions at a freestream Mach number of 2.3 using a hybrid turbulence model and large-eddy simulations. The research findings indicate that the sweep angle has a significant effect on the structures and pressure fluctuations.
AEROSPACE SCIENCE AND TECHNOLOGY
(2022)
Article
Mechanics
J. M. F. Peter, M. J. Kloker
Summary: This article introduces the research on film cooling technology for the nozzle extension of rocket engines. By conducting basic experiments and numerical simulations, several new influencing factors have been identified, which are of great guidance for improving cooling modeling and simulation.
Article
Engineering, Aerospace
Pengcheng Cui, Hongyin Jia, Jiangtao Chen, Guiyu Zhou, Xiaojun Wu, Mingsheng Ma, Huan Li, Jing Tang
Summary: This paper investigates the computational simulation of unsteady multi-body separation characteristics and flow characteristics of hypersonic shroud separation at Mach 7.0. The study identifies various vortexes and shock waves generated during the separation process and discovers the unsteady expansion-transfer-dissipation process of an A-type vortex. The findings provide useful insights for the design of near-space hypersonic vehicles.
Article
Engineering, Aerospace
John-Paul Mosele, Andreas Gross, John Slater
Summary: Wall-resolved implicit large-eddy simulations were performed to study the shock wave boundary layer interactions on a cylindrical test section with different centerbody radii. The results show that the separation of the boundary layer is more significant for larger centerbody radius. Frequency spectra analysis reveals the presence of low-frequency and mid-frequency features near the separation shock and downstream of separation. Proper orthogonal decomposition analysis captures spanwise and streamwise coherent structures in the interaction region.
Article
Engineering, Aerospace
Shu-zi Yang, Wen-zhong Xie, Zhen-yu Wang, Jun Hu, Shengmin Guo
Summary: This paper presents a generalized scaling analysis of separation zones induced by shock wave-turbulent boundary layer interactions (SWTBLIs), considering the downstream expansion fan. The size of the separation zone is found to be closely related to the pressure increase at the reattachment point. The scaling correlation, normalized by the displacement thickness of the incoming boundary layer and the dynamic pressure of the incoming free stream, fits a wide range of experimental and numerical data.
JOURNAL OF AEROSPACE ENGINEERING
(2023)
Article
Thermodynamics
Fanjie Meng, Kunhang Li, Penghua Guo, Jiuliang Gan, Jingyin Li
Summary: This study investigates the variations of shock-wave boundary layer interaction (SBLI) phenomena in a highly loaded transonic compressor cascade. Experimental and numerical methods were used to observe and analyze the shock structure, pressure distribution, and shock oscillation characteristics. It was found that the shock wave patterns and behaviors are significantly affected by the increase in incoming Mach number and the presence of SBLI-induced separation bubble.
JOURNAL OF THERMAL SCIENCE
(2023)
Article
Engineering, Aerospace
Dequan Xu, Shibin Luo, Jiawen Song, Jian Liu, Wenbin Cao
Summary: This paper proposes a parallel algorithm based on multiple graphics processing units to improve parallel efficiency in large-scale grid computing, verifies the accuracy and feasibility of the algorithm, and applies it to direct numerical simulation of shock wave boundary layer interference research.
Article
Engineering, Aerospace
Changsheng Wang, Qitai Eri, Bo Kong, Yong Wang, Wenhao Ding
Summary: A novel simplified numerical simulation method was developed to estimate the bleed mass flow rate and simulate the flowfield structure in the bleed region in supersonic inlets. The method employed Prandtl-Meyer expansion theory to calculate the location of the barrier shock and reconstruct the flow structure inside the bleed hole. A discrimination algorithm was developed to distinguish the grids connected to the bleed hole in the bleed zone. The method was evaluated and found to be in good agreement with experimental data.
Article
Mechanics
Xin Li, Yue Zhang, Huijun Tan, Shu Sun, Hang Yu, Yi Jin, Jie Zhou
Summary: This study experimentally and analytically investigates the length scaling for the boundary layer separation induced by two incident shock waves in a Mach 2.73 flow. The experimental results show that the separation point moves downstream with increasing shock wave distance. For the dual-incident shock wave-turbulent boundary layer interactions exhibiting a coupling separation state, the upstream interaction length approximately linearly decreases with increasing distance, and the decrease rate increases with the second deflection angle. A prediction method for the upstream interaction length is proposed, with a relative error of about 10% compared to the experimental result.
JOURNAL OF FLUID MECHANICS
(2023)
Article
Mechanics
Wei Xie, Zhenbing Luo, Lin Hou, Yan Zhou, Qiang Liu, Wenqiang Peng
Summary: This study investigates the performance of a plasma synthetic jet actuator with Laval-shaped and straight-shaped exits. It shows that the drag reduction effect of a PSJA with a Laval-shaped exit is significantly better than that of one with a straight-shaped exit under certain conditions, with the optimal drag reduction values achieved at different epsilon levels.
Article
Mechanics
Yizhou Wang, Haideng Zhang, Yun Wu, Yinghong Li, Yujie Zhu
Summary: This paper investigates the flow control effects of nanosecond dielectric barrier discharge (NS-DBD) plasma actuation on the supersonic compressor cascade flow at low Reynolds numbers through large-eddy simulations. The study shows that NS-DBD plasma actuation induces a distorted flow structure (DFS) on both the blade pressure surface and suction surface. Despite being suppressed by shock waves on the blade pressure surface, the DFS still triggers instability in the shear layer. The study also finds that the DFS on the blade pressure surface suppresses shock-wave-induced large-scale flow separation and reduces the overall total pressure loss of the blade passage by 7.4%.
Article
Mechanics
Xin Li, Yue Zhang, Huijun Tan, Yi Jin, Chao Li
Summary: This study investigates the interactions between the boundary layer and two successive incident shock waves in supersonic mixed-compression inlets. Experimental and analytical methods are used to study the turbulent boundary layer separation induced by single and dual shock waves. The study reveals different flow features and separation region shapes depending on the distance between the shock waves.
JOURNAL OF FLUID MECHANICS
(2022)
Article
Engineering, Aerospace
Qiang Liu, Zhenbing Luo, Lin Wang, Guohua Tu, Xiong Deng, Yan Zhou
Summary: Direct numerical simulations were conducted on a spatially developing Ma 2.25 supersonic turbulent boundary layer with streamwise-striped wall blowing for turbulence drag reduction. It was found that despite weak control amplitudes, SSB can result in drag reduction effects. Analysis using compressible Renard-Deck decomposition revealed that the spatial growth term is mainly responsible for turbulence drag reduction.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Mechanics
Wen-Zhong Xie, Shu-Zi Yang, Qing-Wei Zhao, Qing Zhang, Shengmin Guo
Summary: This study predicts shock wave/turbulent boundary layer interactions (SWTBLIs) using numerical methods and generates detailed flow field data. A model for predicting the scale of SWTBLI separation bubble is proposed based on momentum balance, and essential correlations for key physical quantities are provided. The experimental results confirm the accuracy of the model.
EUROPEAN JOURNAL OF MECHANICS B-FLUIDS
(2022)