Effects of back pressure fluctuation on pseudo-shock waves in a rectangular duct

Deng, Ruoyu; Kim, Heuy Dong; Chen, Qijun

doi:10.1007/s12206-020-1023-5

Cited by 3 publications

(2 citation statements)

References 11 publications

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“…Meanwhile, the vortices generated by the shear layer of the separation bubble travel downstream and have a direct influence on the motion of the downstream shocks. Similarly, other studies [193][194][195] demonstrate that pressure perturbations travel upstream to the leading-edge shock train through the subsonic flow region near the wall, triggering shock fluctuations. Leonard and Narayanaswamy [196] investigated the shock dynamics in a two-dimensional axisymmetric isolator with an incoming Mach number of 3.0.…”

Section: Effect Of Back Pressurementioning

confidence: 60%

See 1 more Smart Citation

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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Section: Effect Of Back Pressurementioning

confidence: 60%

“…Deng et al [193] revealed that a phase difference exists between the back pressure fluctuation and the leading-edge shock train oscillation, which increases gradually with increasing the excitation frequency. The leading-edge shock train oscillation amplitude is reduced with an increase in the phase difference.…”

Section: Effect Of Back Pressurementioning

confidence: 99%