Aerothermodynamics of a hypersonic vehicle with a forward-facing parabolic cavity at nose

Yadav, Rajesh; Güven, Uğur

doi:10.1177/0954410013498056

Cited by 9 publications

(5 citation statements)

References 14 publications

(21 reference statements)

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“…On the other hand, air downstream of the fore shock creates an annular vortex structure around the inner lip of the cavity. This vortex acts to isolate the new stagnation zone (inside the cavity) from the high-enthalpy flow upstream [225]. For both deep and shallow cavities, a local excessive heat flux is attained at the lip of the cavity that may exceed that at the stagnation point of the forebody without the cavity.…”

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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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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“…The influence of a forward-facing cavity on heat transfer and aerodynamic coefficients has been investigated by Saravanan et al (2009), and the deepest cavity shows better heat flux reduction (Silton and Goldstein, 2005;Lu and Liu, 2012b;Yadav and Guven, 2014). The mechanism of heat reduction induced by a forward-facing cavity has been by many researchers (Huebner and Utreja, 1993;Engblom et al, 1997), and the cooling effect is produced by the oscillation of the bow shock wave (Ladoon et al, 1998).…”

Section: Combination Of Counterflowing Jet and Forward-facing Cavitymentioning

confidence: 99%

A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations

Huang

2015

J. Zhejiang Univ. Sci. A

114

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Drag reduction and thermal protection is very important for hypersonic vehicles, and a counterflowing jet and its combinations is one of the most promising drag and heat release reduction strategies. In the current survey, research progress on the drag and heat release reduction induced by a counterflowing jet and its combinations is summarized. Three combinatorial configurations are considered, namely the combination of the counterflowing jet and a forward-facing cavity, the combination of the counterflowing jet and an aerospike, and the combination of the counterflowing jet and energy deposition. In conclusion, some recommendations are provided, especially for jet instability protection, for the tradeoff between drag and heat release reductions, and for the critical points for the operational and geometric parameters in the flow mode transition.

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“…Hypersonic vehicles such as hypervelocity projectiles, re-entry vehicles and hypersonic aircraft are designed to withstand severe heat loads. A proposed heat transfer reduction mechanism is to locate a forward-facing cavity at the nose tip [1][2][3][4][5]. It was reported that the heat flux at the cavity base could be as little as 2 to 10 times less than the stagnation point of a conventional convex hemispherical tip [6].…”

Section: Introductionmentioning

confidence: 99%

Prediction of Shock-Standoff Distance and Entropy Distribution for Forward-Facing Cavity

Wang¹

2018

IJASS

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Experiments are performed on a cylinder with a forward-facing cavity at M ∞ = 10 in the FD-14A shock tunnel. The shock-standoff distance and oscillation characteristics are recorded by a high-speed movie, and the dynamic pressure transducer is used to capture the unsteady signal of cavity base. Based on experimental and numerical results, a prediction method for estimating the shock-standoff distance is proposed. Results of shock-standoff distance and oscillation frequency are obtained for experiments in the shock tunnel. The predicted oscillation frequency is in accordance with experimental results. Furthermore, the relation of shock shape and the entropy increase are combined to obtain the characteristics of entropy distribution. As the shock-shape of flat-nosed cylinders is more liable to be influenced than blunt-nosed cylinders with increasing Mach number, the location of the extreme value moves to the surface as the Mach number increases for flat-nosed cylinders, while it remains the identical location for blunt-nosed cylinders.

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Aerothermodynamics of a hypersonic vehicle with a forward-facing parabolic cavity at nose

Cited by 9 publications

References 14 publications

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

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

A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations

Prediction of Shock-Standoff Distance and Entropy Distribution for Forward-Facing Cavity

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