Investigation on cooling effect with a combinational opposing jet and platelet transpiration concept in hypersonic flow

Shen, BinXian; Yin, Liang; Zhang, Xiaoli; Liu, Weiqiang

doi:10.1016/j.ast.2018.11.021

Cited by 34 publications

(5 citation statements)

References 24 publications

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“…226 It is numerically explored that implementation of platelet transpiration added with opposing jet cooling capability and to enhance the jet effectiveness. 227,228…”

Section: Active Techniquesmentioning

confidence: 99%

“…226 It is numerically explored that implementation of platelet transpiration added with opposing jet cooling capability and to enhance the jet effectiveness. 227,228 Possible gaps and issues in the practical implementation of the opposing jet. A large amount of study has been done on opposing jets, but the implementation of real supersonic or hypersonic flight conditions (at high Mach and high altitude) were rarely considered.…”

Section: Counter-flow Jetsmentioning

confidence: 99%

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Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Rashid

Nawaz

Maqsood

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Typical challenges of supersonic flight include wave drag, acoustic signature, and aerodynamic heating due to the formation of shock waves ahead of the vehicle. Efforts in the form of sleek aerodynamic designs, better propulsion systems, and the implementation of passive and active techniques are generally adopted to achieve a weaker shock wave system. Shock reduction can improve flight range, reduce fuel consumption, and provide thermal protection of the forebody region. This paper briefly reviews shock reduction techniques, including passive, active, and hybrid flow control. Airfoil shape optimization, mechanical spike, and forebody cavities are studied as passive flow control approaches. For active flow control, developments in the area of opposing jets and energy deposition are explored. The combination of active and passive flow control and the hybrid flow techniques are discussed in the end. The discussions include the principle of operation, physics of fluid behavior, and overall contribution to flight stability characteristics. The implications in the usage of these technologies, along with potential gaps, are also identified. This comprehensive review can serve as the basis for contemporary solutions to realize sustainable supersonic travel for the aviation industry.

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“…226 It is numerically explored that implementation of platelet transpiration added with opposing jet cooling capability and to enhance the jet effectiveness. 227,228…”

Section: Active Techniquesmentioning

confidence: 99%

Section: Counter-flow Jetsmentioning

confidence: 99%

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Rashid

Nawaz

Maqsood

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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show abstract

“…Similar devices were examined by the group of Huang as jet aperture and multiple orifices at the leading edges of a waverider [200,201] and hypersonic vehicle [202] configurations. Multiple orifices over-performed the single aperture while especially with odd number of orifices since an orifice was placed at the A pposing jet device with platelet transpiration passive cooling device was explored numerically by Yisheng et al [203] and then by Shen et al [204], [205] for different freestream and operating conditions. Adding the transpiration cooling capability further enhanced the opposing jet effectiveness (in terms of reattachment peak heat flux) with a small added mass flow rate penalty.…”

Section: Non-conventional Studies On Counterflow Jetsmentioning

confidence: 99%

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Ahmed

Qin

2020

Progress in Aerospace Sciences

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One key feature that distinguishes the flowfield around vehicles flying in supersonic and hypersonic regimes is the bow shock wave ahead of forebody. The severe drag and aeroheating impacting these vehicles can be significantly reduced if the bow shock wave ahead of the vehicles forebodies is controlled to yield weaker system of oblique shocks. Benefits of forebody shock control include increasing flight ranges, economizing fuel consumption, reducing dead weights, and thermally protecting forebody structure and onboard equipment. Forebody shock control that has been widely studied since the early 1900s is achievable in numerous techniques that vary according to the mechanism of control. While some of these techniques have already been implemented in real systems, other techniques involve serious complications and tough trade-offs. The present paper is intended to serve as the first comprehensive survey on the field of forebody shock control devices. The objectives of the present paper are multifold. The paper categorizes the various forebody shock control devices in a physics-based manner, explains the underlying physics for each device, and surveys the key studies and state-of-the-art knowledge. The paper also addresses the existing gaps in knowledge, highlights the existing systems implementing these devices, and discusses the associated practical implementation issues and design-tradeoffs. 2. Structural devices, the mechanical spikes: 2.1. Principle of operation of mechanical spikes Drag and Aeroheating Reduction Devices Fluidic Devices Opposing jets Structural Devices Mechanical spikes Energetic Devices Energy deposition Basic devices Structural-Fluidic Devices Structural-Energetic Devices Hybrid devices

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“…In most cases, tangential jet has higher cooling efficiency and longer cooling length (Zuo et al 2017). Opposing jet is a hot spot of research in recent years (Shen et al 2019), but it is mainly used for cooling at stagnation areas, and its corresponding cooling length is shorter compared with tangential cooling jet. Increasing the slot height can also improve the cooling effectiveness (Peng et al 2015), who's essence is to increase the mass flow rate and the thickness of the cooling film.…”

Section: Introductionmentioning

confidence: 99%

Effects of feeding pressures on the flowfield structures of three-dimensional film cooling

Zhao¹,

Yi²,

Mo³

et al. 2022

Fluid Dyn. Res.

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A Mach 2.6 annular supersonic nozzle was designed to protect a hypersonic cone. The annular nozzle is able produce tangential cooling film around the cone. Experiments were carried out in a hypersonic wind tunnel under different cooling film feeding pressures and different attack angles. Temperature-sensitive paint (TSP) was used to measure surface temperature of the cone body; schlieren method was applied to visualize the flow structures. TSP results showed that cooling film can obviously decrease surface heating load, but its efficiency was influenced by the angle of attack (AoA). Schlieren results showed that the shape of upper-lip shock wave is similar to an arc, and the reflected shock wave is more closer to a straight line; both the tilt rate of upper-lip shock wave and the reflected shock wave were increased exponentially with the rise of feeding pressure; a higher feeding pressure resulted in a larger curvature of upper-lip shock wave; compared with reflected shock wave, upper-lip shock wave and shearing layer were more easily affected by the feeding pressure. With higher feeding pressure, incidence point was moved to the further downstream location, and a fitting formula is given to express the relationship between the position of the shock wave incidence point and the feeding pressure.

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Investigation on cooling effect with a combinational opposing jet and platelet transpiration concept in hypersonic flow

Cited by 34 publications

References 24 publications

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Effects of feeding pressures on the flowfield structures of three-dimensional film cooling

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