Fluid-thermal analysis of aerodynamic heating over spiked blunt body configurations

Qin, Qihao; Xu, Jinglei; Guo, Shuai

doi:10.1016/j.actaastro.2016.12.037

Cited by 69 publications

(17 citation statements)

References 32 publications

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“…Their findings were independently supported by Kenworthy [40] and Panaras [45,89] and confirmed by Zapryagaev et al [90,91]. Hankey and his co-researchers conducted experimental and numerical investigation of pulsation of flow around spiked truncated cone [41,92] whereas Morgenstern [34] extended their simulations at higher incidence (up to 10 degrees). Feszty et al [93,94] confirmed using the numerical simulations the findings of Kenworthy.…”

Section: Key Studies On Flow Unsteadiness Associated With Mechanical mentioning

confidence: 72%

“…The mechanism of aeroheating to the forebody is explained by the geometry of flow at reattachment (impingement angle of the dividing streamline) [33], the energy level of the shear layer, and vortex structure inside the recirculation zone [30]. At the spike/ aerodisk tip, excessive thermal loads are witnessed that have remarkable impact on the flowfield structure and device effectiveness [34].…”

Section: Figure 3 Macroscopic Features Of the Flowfield Around Of A Smentioning

confidence: 99%

“…-The transients associated with accelerating and decelerating vehicles during flight were briefly investigated by Qin et al [34] and can invoke more studies. Inclusion of the variation in flight altitude as well as speed to account for real accelerating ascent/ descent of the vehicle is recommended.…”

Section: Prospective Gaps In the Field Of Mechanical Spikesmentioning

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: Key Studies On Flow Unsteadiness Associated With Mechanical mentioning

confidence: 72%

Section: Figure 3 Macroscopic Features Of the Flowfield Around Of A Smentioning

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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“…They investigated the air-flow over the conical, disk, and flat spiked bodies and analyzed the flow asymmetry around axisymmetric spiked blunt bodies at hypersonic regimes. Qin et al [26] conducted a loosely coupled fluid-thermal method to explore the aerodynamic thermal responses of a spiked blunt in a hypersonic regime and relevant flow variation.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Aerothermal Analysis of a Cone-Cylinder Flight Body

Zhang

Jia

Mkumbuzi

et al. 2020

International Journal of Aerospace Engineering

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Exploring the aerothermal characteristic of a flight body has great military applications in tracking, locating, thermal protection, and infrared stealth technologies. Available studies are mostly focused on the transient aerothermal characteristics of vehicles in some specific flight datum, which are not able to satisfy the requirements in real-time tracking for an infrared system. This paper probes into a method of dynamic thermal analysis of a cone-cylinder flight body with a high spinning speed. Firstly, a theoretical model for analyzing the dynamic aerothermal characteristics is established using the thermal node-network method. Then, trajectory datum and the convective heat-transfer coefficients are solved simultaneously. Besides, the trajectory datum in supersonic, transonic, and subsonic regimes is separately defined as the boundary conditions, and fluid-thermal analysis methods are implemented by a combination of sliding mesh and multicoordinate approaches. Finally, the flow characteristics are analyzed and compared with disregarding the rotational speed. The results demonstrate that there are significant differences between the two cases, especially at the high-speed regimes. This study further confirms that it is essential to conduct the aerothermal analysis from a dynamic point of view, and taking the impacts of coupling motion into account is also of vital importance.

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“…Drag reduction of the order 86 to 90% was reported at M = 6:0 by Eghlima and Mansour [15] through computations, adopting a combination of spike and counter ow jet. Thermal analysis of spikes at M = 5:0 with di erent shapes and diameters was carried out by Qin et al [16]. Numerical simulations with series of aerospikes at M = 10:0 were performed by Yadav et al [17], which reported a maximum drag reduction of 44%.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic Flow over Hemispherical Blunt Body with Spikes

2018

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Abstract. Use of spike on a hemispherical body changes the ow eld and hence, the aerodynamic drag. Computational studies have been carried out to obtain the ow eld around a hemispherical body with spikes at a hypersonic Mach number of 6. The e ect of shape of spike tip and length has been studied. Laminar computations have been made adopting structured grid using commercial software FLUENT. It is observed that use of a sharp spike itself reduces the drag signi cantly. However, the use of a hemispherical head spike further reduces the drag. Contribution of di erent components towards drag indicates that the increase in length of a spike does not change the spike contribution. However, the ow eld on main body is altered, which leads to reduction in drag with change in length. The estimated maximum drag is found to be highest among all reported drag values with any spike shape and length in the literature.

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Fluid-thermal analysis of aerodynamic heating over spiked blunt body configurations

Cited by 69 publications

References 32 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

Dynamic Aerothermal Analysis of a Cone-Cylinder Flight Body

Hypersonic Flow over Hemispherical Blunt Body with Spikes

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