A preliminary investigation of the Helmholtz resonator concept for heat flux reduction

Yuceil, B.; Dolling, D. S.; Wilson, David J.

doi:10.2514/6.1993-2742

Cited by 26 publications

(7 citation statements)

References 1 publication

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“…Yuceil et al 120,121,122 examined the effect of important geometric parameter L/D (ratio of length-to-diameter of cavity) for hemispherical blunt body at Mach 4 . 9.…”

Section: Passive Flow Control Techniquesmentioning

confidence: 99%

“…However, the shock standoff distance depended on nose size instead of cavity depth. 119 Yuceil et al 120,121,122 examined the effect of important geometric parameter L/D (ratio of length-to-diameter of cavity) for hemispherical blunt body at Mach 4.9. The authors suggested that if L/D was less than 0.4, then the cavity is shallow; for intermediate cavity, L/D was between 0.4 and 0.7; and for the deep cavity, L/D was greater than 1.…”

Section: Basic Operational Principlementioning

confidence: 99%

“…At the same time, the pressure inside the cavity decreased and provided a cooling effect. By increasing the length-to-diameter ratio (L/D) of the cavity, a significant decrease in oscillation frequency was reported 128,121 that causes a decrease in heat flux inside the cavity even at different altitudes in supersonic Mach. 130 However, for steady oscillations, the critical value of length-to-diameter ratio (L/D) was 1.2 beyond this critical value flow unsteadiness enhanced.…”

Section: Basic Operational Principlementioning

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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“…Yuceil et al 120,121,122 examined the effect of important geometric parameter L/D (ratio of length-to-diameter of cavity) for hemispherical blunt body at Mach 4 . 9.…”

Section: Passive Flow Control Techniquesmentioning

confidence: 99%

Section: Basic Operational Principlementioning

confidence: 99%

Section: Basic Operational Principlementioning

confidence: 99%

See 1 more Smart Citation

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

“…The mechanism of aeroheating reduction differs in deep cavities from that in shallow cavities. A deep cavity acts as an organ pipe along which the column of air downstream of the fore shock wave oscillates in its natural frequency [220][221][222]. This oscillation causes the fore shock wave to oscillate yielding a cooling effect.…”

Section: Combined Jet-cavity Devicementioning

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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“…Preliminary experiments, using an infrared (IR) camera, by Yuceil et al [11] indicated that large diameter, shallow cavities (length-to-diameter ratio (L/D) between 0.15 and 0.35) created a stable 'cool ring', just outside of a sharp cavity lip, with temperatures locally lower than those found on a simple spherical nose. A joint numerical and experimental study by Engblom [3] concluded that sharp cavity lips produce not only a separated recirculation region (accounting for the 'cool ring') but also severe heating just inside the cavity for weakly oscillating flows.…”

Section: Introductionmentioning

confidence: 99%

Numerical and experimental investigation of the reduction of hypersonic nose tip ablation

Silton

Goldstein

1998

36th AIAA Aerospace Sciences Meeting and Exhibit

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To reduce the severe heating and ablation at the nose tip of a hypersonic vehicle, the introduction of a forward-facing cavity into the nose tip is explored. In the present joint numerical/experimental study, the effects of the cavity on ablation are explicitly addressed whereas previous studies have concentrated on heating rates alone. While the study is continuing, initial results look promising. Numerical and experimental results agree surprisingly well for a baseline hemisphere cylinder case.

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A preliminary investigation of the Helmholtz resonator concept for heat flux reduction

Cited by 26 publications

References 1 publication

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

Numerical and experimental investigation of the reduction of hypersonic nose tip ablation

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