Detailed parametric investigations on drag and heat flux reduction induced by a combinational spike and opposing jet concept in hypersonic flows

Ou, Min; Yan, Li; Huang, Wei; Li, Shibin; Li, Lang-quan

doi:10.1016/j.ijheatmasstransfer.2018.05.013

Cited by 163 publications

(14 citation statements)

References 67 publications

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“…Adding a jet at the tip of an aerodisk rather than the tip of a plain spike was proposed by Ou et al [317,318]. Different jet pressures and radial locations on the base of forward and intermediate aerodisks along the spike were examined.…”

Section: Structural-fluidic Devicesmentioning

confidence: 99%

“…In addition, concerns can be raised regarding the credibility of some reported conclusions in the numerical simulation studies so far. Due to the lack of experimental database, some simulation studies used experiments on isolated spikes, conventional opposing jets, or even plain blunt forebodies [314][315][316][317]328] to validate simulation techniques. Other simulation studies did not include any validation with experiments at all [313,314,323,324,329].…”

Section: Comments On Structural-fluidic Devicesmentioning

confidence: 99%

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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: Structural-fluidic Devicesmentioning

confidence: 99%

Section: Comments On Structural-fluidic Devicesmentioning

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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“…Various parametric studies on spike mounted hemispherical bodies related to drag reduction have also been reported in the recent past [4][5][6][7][8][9][10]. With increasing the spike length up to a critical length, the amount of drag reduction has been reported to increase [4].…”

Section: Introductionmentioning

confidence: 99%

Effect of intermediate aerodisk mounted sharp tip spike on the drag reduction over a hemispherical body at Mach 2.0

Tembhurnikar¹,

Jadhav²,

Sahoo³

2020

FME Transactions

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Reduction of forebody drag in high speed flying vehicles such as rockets and missiles are of high research interest in the present time. In the present research, drag reduction obtained by using an intermediate aerodisk mounted sharp tip spike has been investigated using computational studies at Mach number of 2.0. The flowfield over a hemispherical blunt body with an intermediate aerodisk mounted sharp tip spike is investigated at zero degree angle of attack and the amount of drag reduction obtained is then compared with that of a conventional sharp tip spike mounted hemisphere. The presence of an intermediate aerodisk changes the flow physics and shock system over the blunt body. The change in the system of shock waves by mounting an intermediate aerodisk results in a higher percentage (20% higher) of drag reduction generated by the blunt spiked body moving at a supersonic speed of Mach 2.0. Use of intermediate aerodisk proves to be beneficial in terms of drag reduction for spike lengths ranging beyond the critical length.

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“…Zhou et al studied a series of problems of reverse jet drag reduction of the shape of a supersonic blunt body and concluded that the effect of drag reduction and heat reduction is affected by the total pressure ratio of the jet, the flight angle of attack, and the size of the nozzle [19][20][21]. Huang et al gave a more detailed overview of the reverse jet and related technologies [22,23] and studied the length of the rectifier cone and the pressure ratio of the reverse jet to reduce the resistance and heat resistance of the rectifier cone [24]. And the effect of porous reverse jet on drag and heat reduction of high-speed aircraft [25,26].…”

Section: Introductionmentioning

confidence: 99%

Research on Control Technology of Jet and Rectifying Cone Combined Flow Field

Lei

Wang

et al. 2020

International Journal of Aerospace Engineering

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As an active flow field control technology, reverse jet and rectifier cone can significantly affect the flow field around the high-speed aircraft and reduce the drag and heat of high-speed aircraft to a certain extent. In this paper, the CFD numerical method is used to simulate and analyze the flow around the bluff body front rectifier cone and the reverse jet interference flow field. Further considering the combination of the two, the flow field structure around the bluff body under the combination of rectifying cone and reverse jet flow was simulated. Research shows, for the flow field of a single reverse jet, the pressure ratio of the reverse jet to the main flow has a significant effect on the drag reduction performance. With the change of the pressure ratio of the jet to the main flow, two modes of long jet and short jet will appear. The structure of the short jet modal flow field is relatively stable. However, with the increase of attack angle, the shear layer of free flow will attach to the shock wave and form hot spot, which is a great threat to high-speed aircraft. When the rectifier cone and the reverse jet are combined, within a certain angle of attack, the wall will not form a reattachment shock wave. The area behind the bow shock and in front of the aircraft head is a free-state zone, which has a good cooling effect on the aircraft head. At the same time, the static pressure on the wall is reduced, which has a very good drag reduction effect.

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Detailed parametric investigations on drag and heat flux reduction induced by a combinational spike and opposing jet concept in hypersonic flows

Cited by 163 publications

References 67 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

Effect of intermediate aerodisk mounted sharp tip spike on the drag reduction over a hemispherical body at Mach 2.0

Research on Control Technology of Jet and Rectifying Cone Combined Flow Field

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