A survey on numerical simulations of drag and heat reduction mechanism in supersonic/hypersonic flows

Sun, Xi-wan; Huang, Wei; Ou, Min; Zhang, Ruirui; Li, Shibin

doi:10.1016/j.cja.2018.12.024

Cited by 115 publications

(12 citation statements)

References 73 publications

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“…In [11], Ahmed and Qin presented a comprehensive survey on previous studies and latest contributions (up to 2010) for mechanical spike devices. The research group of Huang contributed with four review articles [12][13][14][15]. In [12], focus was made on opposing jet technique and its combinations with forward-facing cavity, energy deposition, and spikes.…”

Section: Figure 2 Physics-based Classification Of Drag and Aeroheatinmentioning

confidence: 99%

“…In [12], focus was made on opposing jet technique and its combinations with forward-facing cavity, energy deposition, and spikes. Survey on experimental and numerical simulation studies on these techniques and their combinations was presented separately in [13] and [14], respectively. In [15], a concise survey on spikes and their combinations was presented.…”

Section: Figure 2 Physics-based Classification Of Drag and Aeroheatinmentioning

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: Figure 2 Physics-based Classification Of Drag and Aeroheatinmentioning

confidence: 99%

Section: Figure 2 Physics-based Classification Of Drag and Aeroheatinmentioning

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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“…At present, the technologies about the shock wave drag reduction and thermal protection of aircraft can be divided into two categories: passive control and active control according to whether there exist energy consumption during control and the control loop mode [1], including the aerospike, energy deposition, forward-facing cavity, opposing jet, and other drag reduction and thermal protection schemes and their combinational concepts. The articles by Ahmed, Qin [2], and Sun et al [3] summarize the current research progress of the supersonic and hypersonic drag reduction and thermal protection methods. Among these techniques, attaching an aerospike at the top of the supersonic vehicle proved to be an efficient and simple way to accomplish a significant reduction in drag and aerodynamic heating [4].…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Supersonic Carman Curve Bodies with Aerospike

Zhao

Peng

et al. 2021

International Journal of Aerospace Engineering

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Drag reduction is one of the important problems for the supersonic vehicles. As one of the drag reduction methods, aerospike has been used in some equipment because of its good drag reduction effect. In this paper, the numerical simulations of Carman curve bodies with different lengths of the aerospike and different radius of the flat cylindrical aerodisk in supersonic flow freestream are investigated. Based on the numerical simulations, the mechanism of drag reduction of the aerospike is discussed. The drag reduction effect influence of the parameters of the aerodisk radius and the aerospike length on the Carman curve body is analyzed. The aerodisk radius within a certain range is helpful for the drag reduction. The change of length of the aerospike has little effect on the drag of Carmen curve bodies. The drag reduction effect of the same aerospike becomes worse with the increase of the incoming Mach number.

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“…In 2018, Badiger and Saravanan (6) studied the heat flux characteristics within and outside a forward-facing cavity using the shock tunnel experiments, and the frequency analysis for flow oscillations was performed using the fast Fourier transformation. Later, Sun et al (7) summarised the research progress on their drag and heat flux reduction mechanisms from the point of view of numerical simulation, and the research information on the combinational concepts have been provided at the end of this survey.…”

Section: Introductionmentioning

confidence: 99%

Influences of lateral jet location and its number on the drag reduction of a blunted body in supersonic flows

Liao

et al. 2020

Aeronaut. j.

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The analysis of the aerodynamic environment of the re-entry vehicle attaches great importance to the design of the novel drag reduction strategies, and the combinational spike and jet concept has shown promising application for the drag reduction in supersonic flows. In this paper, the drag force reduction mechanism induced by the combinational spike and lateral jet concept with the freestream Mach number being 5.9332 has been investigated numerically by means of the two-dimensional axisymmetric Navier-Stokes equations coupled with the shear stress transport (SST) k-ω turbulence model, and the effects of the lateral jet location and its number on the drag reduction of the blunt body have been evaluated. The obtained results show that the drag force of the blunt body can be reduced more profoundly when employing the dual lateral jets, and its maximum percentage is 38.81%, with the locations of the first and second lateral jets arranged suitably. The interaction between the leading shock wave and the first lateral jet has a great impact on the drag force reduction. The drag force reduction is more evident when the interaction is stronger. Due to the inclusion of the lateral jet, the pressure intensity at the reattachment point of the blunt body decreases sharply, as well as the temperature near the walls of the spike and the blunt body, and this implies that the multi-lateral jet is beneficial for the drag reduction.

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A survey on numerical simulations of drag and heat reduction mechanism in supersonic/hypersonic flows

Cited by 115 publications

References 73 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

Numerical Simulation of Supersonic Carman Curve Bodies with Aerospike

Influences of lateral jet location and its number on the drag reduction of a blunted body in supersonic flows

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