A review of the shock-dominated flow in a hypersonic inlet/isolator

Huang, He-xia; Tan, Hui-jun; Li, Fang-bo; Tang, Xue-bin; Qin, Yuan; Xie, Li-Bin; Xu, Yao-Yu; Li, Can-min; Gao, Si-min; Zhang, Yue; Sun, Shu; Zhao, Dan

doi:10.1016/j.paerosci.2023.100952

Cited by 10 publications

(3 citation statements)

References 192 publications

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“…The inlet/isolator's maximum sustainable backpressure is a crucial characteristic. Moreover, the throttling process often results in complex shock train phenomena [33][34][35]. For the inlet/isolator in this study, the maximum sustainable backpressure ratio is 195 times the incoming static pressure (p0) without wind shear.…”

Section: Effect Of Wind Shear On Shock Trainmentioning

confidence: 95%

“…The hypersonic inlet/isolator, an essential component of the scramjet engine, plays a significant role in the stable and safe operation of aircraft [1][2][3][4][5][6][7]. During flights, because of the complex wind field environment [8][9][10][11], aircraft frequently encounter atmospheric disturbances, such as gusts, wind shear, three-dimensional wind, vortices, and continuous turbulence.…”

Section: Introductionmentioning

confidence: 99%

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Transient Flow Evolution of a Hypersonic Inlet/Isolator with Incoming Windshear

Gao,

Huang,

Meng

et al. 2023

Aerospace

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In this paper, a novel flow perturbation model meant to investigate the effects of incoming wind shear on a hypersonic inlet/isolator is presented. This research focuses on the transient shock/boundary layer interaction and shock train flow evolution in a hypersonic inlet/isolator with an on-design Mach number of 6.0 under incoming wind shear at high altitudes, precisely at an altitude of 30 km with a magnitude speed of 80 m/s. Despite the low intensity of wind shear at high altitudes, the results reveal that wind shear significantly disrupts the inlet/isolator flowfield, affecting the shock wave/boundary layer interaction in the unthrottled state, which drives the separation bubble at the throat to move downstream and then upstream. Moreover, the flowfield behaves as a hysteresis phenomenon under the effect of wind shear, and the total pressure recovery coefficients at the throat and exit of the inlet/isolator increase by approximately 10% to 12%. Furthermore, this research focuses on investigating the impact of wind shear on the behavior of the shock train. Once the inlet/isolator is in a throttled state, wind shear severely impacts the motion of the shock train. When the downstream backpressure is 135 times the incoming pressure (p0), the shock train first moves upstream and gradually couples with a cowl shock wave/boundary layer interaction, resulting in a more significant separation at the throat, and then moves downstream and decouples from the separation bubble at the throat. However, if the downstream backpressure increases to 140 p0, the shock train enlarges the separation bubble, forcing the inlet/isolator to fall into the unstart state, and it cannot be restarted. These findings emphasize the need to consider wind shear effects in the design and operation of hypersonic inlet/isolator.

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Section: Effect Of Wind Shear On Shock Trainmentioning

confidence: 95%

Section: Introductionmentioning

confidence: 99%

Transient Flow Evolution of a Hypersonic Inlet/Isolator with Incoming Windshear

Gao,

Huang,

Meng

et al. 2023

Aerospace

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“…Nevertheless, there is an extensive body of research dedicated to better understanding these phenomena; overviews of SBLIs and pseudo-shock waves in high-speed intakes were published by Gaitonde [172] and Gnani et al [173]. Another more recent publication by Huang et al [174] describes the behaviour of shock trains in isolators, highlighting the initiation of the unstable state when the shock train interacts with background waves. The onset of this instability occurs when the interaction point aligns with the front section of the background shock, coupled with the leading shock that shifts the separation point forward, thereby altering the configuration of the shock train.…”

Section: Unsteady Shock Trains In Isolatorsmentioning

confidence: 99%

Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration

Philippou,

Zachos,

MacManus

2024

Aerospace

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High-speed air intakes often exhibit intricate flow patterns, with a specific type of flow instability known as `buzz’, characterized by unsteady shock oscillations at the inlet. This paper presents a comprehensive review of prior research, focused on unraveling the mechanisms that trigger buzz and its implications for engine stability and performance. The literature survey delves into studies concerning complex-shaped diffusers and isolators, offering a thorough examination of flow aerodynamics in unstable environments. Furthermore, this paper provides an overview of contemporary techniques for mitigating flow instability through both active and passive flow control methods. These techniques encompass boundary layer bleeding, the application of vortex generators, and strategies involving mass injection and energy deposition. The study concludes by discussing future prospects in the domain of engine-intake aerodynamic compatibility. This work serves as a valuable resource for researchers and engineers striving to address and understand the complexities of high-speed air induction systems.

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Nonlinear aeroelastic behavior of a panel impinged by oscillating shock

He,

Shi,

Dowell

et al. 2024

Nonlinear Dyn

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The aeroelastic responses and nonlinear behaviors of a two-dimensional panel impinged by an oscillating Mach stem shock are investigated through theoretical analysis. Through the nonlinear descriptors, such as Poincaré maps and Largest Lyapunov exponents, the panel with oscillating shock impingement is found to exhibit multiple responses, including single/multi-periodic limit cycle oscillation, quasiperiodic motion, and chaotic motion. Without altering the in-plane force, which is the principal source of structural nonlinearity, the shock oscillation complicates the nonlinear behaviors of the panel. With shock oscillation, the original divergence instability is transformed into post-divergence limit cycle oscillation, and the flutter response exhibits rich nonlinear characteristics. The effect of initial shock impingement location, shock oscillating amplitude, and shock oscillating frequency are disclosed through the bifurcation diagram, which significantly influences the nonlinear character-

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A review of the shock-dominated flow in a hypersonic inlet/isolator

Cited by 10 publications

References 192 publications

Transient Flow Evolution of a Hypersonic Inlet/Isolator with Incoming Windshear

Transient Flow Evolution of a Hypersonic Inlet/Isolator with Incoming Windshear

Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration

Nonlinear aeroelastic behavior of a panel impinged by oscillating shock

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