Hysteresis phenomenon of hypersonic inlet at high Mach number

Jiao, Xiaoliang; Chang, Juntao; Wang, Zhongqi; Yu, Daren

doi:10.1016/j.actaastro.2016.08.025

Cited by 41 publications

(5 citation statements)

References 45 publications

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“…Jiao and Wang conducted systematic research into overrated unstart and clarified the flow characteristics and variation in the regularity of overrated unstart. Furthermore, these researchers also found that the phenomenon of hysteresis also occurs during overrated unstart [38][39][40].…”

Section: Introductionmentioning

confidence: 91%

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

Tang,

Xiong,

Fan

et al. 2023

Applied Sciences

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Intense shock boundary-layer interaction may lead to multiple unstart modes existing in a hypersonic inlet. Thus, self-start problems become complex and cannot be explained using the classical double-solution theory of air inlet. The essence of the self-start process of a hypersonic inlet is the vanishment of separations near or in the inlet. To clarify self-start characteristics, experiments were conducted on three distinct types of unstart mode: the flow mode of small separation on body (SSB), large separation on body (LSB), and dual separations on both body and lip (DSBL); researchers recently discovered these as the unstart modes of hypersonic inlet. The results from the current experiment are as follows: (1) The SSB vanishes by raising the angle of attack (alpha). Before the vanishing point is reached, there is a dwindling process for this separation. (2) The LSB vanishes through acceleration or a decreasing alpha. (3) DSBL are difficult to vanish directly, which results in poor self-start performance. However, the DSBL flow mode may convert to LSB unstart form—which is easier to self-start—by decreasing the alpha. The Flow Field Reconstruction Method was designed to improve the self-start of the DSBL flow mode, and it was validated through experiments. Analysis of the flow mechanism revealed the reason for the poor self-start performance of the DSBL unstart mode: large-scale separation on the lip side cannot be promoted to vanish through broadwise spillage due to the resistance of sideboards. The results of this study could greatly enrich the existing theory of start problems for hypersonic inlets.

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Section: Introductionmentioning

confidence: 91%

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

Tang,

Xiong,

Fan

et al. 2023

Applied Sciences

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“…If the intake operates on a lower Mach number, the intake will unstart [94], and the total pressure recovery and the mass flow captured will be reduced [95]. At an operating Mach number higher than the design value, several studies [75,[96][97][98] have identified that a Mach reflection causes the forward shock propagation and a shock detachment from the cowl lip, referred to as "local unstart".…”

Section: Effect Of Mach Numbermentioning

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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“…Chang et al (2014) proposed a backpressure unstart detection method based on the history of wall static pressures. Jiao et al (2016) studied two general overall wave configurations in hypersonic inlets. Li et al (2018) investigated the unstart/restart properties in turbine-based combined cycle (TBCC) inlets numerically.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of the Unstart/Restart Process of a Two-Dimensional Supersonic Inlet Induced by Backpressure

Zhao

Zhou

Zhao

2022

JAFM

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Unstart/restart phenomena induced by backpressure in a general inlet with a freestream of M = 2.7 are investigated in an in-draft supersonic quiet wind tunnel. The boundary layers are turbulent on the forebody while are laminar on the lip wall, which could mimick real flight conditions. The high-speed Schlieren imaging system and the nanoparticle-based planar laser scattering (NPLS) method are used to visualize the inlet flowfield. The inlet wall pressure is measured by high-frequency pressure transducers. The backpressure is reproduced by downstream transverse jets other than mechanical throttlers, which is more suitable to mimic backpressure caused by combustion. The high spatio-temporal resolution full-view images of inlet flow features during the complete unstart/restart process are captured, which are seldom seen before. The formation and disappearance process of massive boundary layer separation at the entrance of the unstarted inlet is observed. The backpressure transmits upstream through the shock wave/boundary layer interaction (SWBLI) regions. The shock structures change the angles and merge upstream to balance the pressure rise. The Mach shock reflection configuration is observed in both unstart/restart process, accompanied by the boundary layer separation extending to the leading edge. The experiment also revealed notable hysteresis in the unstart/restart process.

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Hysteresis phenomenon of hypersonic inlet at high Mach number

Cited by 41 publications

References 45 publications

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

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

Experimental Study of the Unstart/Restart Process of a Two-Dimensional Supersonic Inlet Induced by Backpressure

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