Aerothermodynamics of generic re-entry vehicle with a series of aerospikes at nose

Yadav, Rajesh; Velidi, Gurunadh; Güven, Uğur

doi:10.1016/j.actaastro.2013.11.015

Cited by 54 publications

(9 citation statements)

References 21 publications

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“…However, an aeroheating penalty upon using such device was reported in [113]. The group of Yadav [28,114,115] -d same concept in which one or two more hemispherical aerodisks are added to locations along the spike stem. Monotonic drop in drag and aeroheating was reported by adding more disks with marginal benefits as the number of disks increases.…”

Section: Non-conventional Studies On Mechanical Spikesmentioning

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: Non-conventional Studies On Mechanical Spikesmentioning

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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“…Further, in order to reduce the amount of drag reduction for the spiked body configuration with a spike of length beyond the critical length (L/D=2.0), an intermediate aerodisk is mounted on the spike stem. The geometry of the intermediate aerodisk used in the present investigation is adopted with reference to the aerodisk used by Yadav et al [15][16]. The point of flow separation over the spike length for longest spike (L/D=2.0) has been considered as the location of mounting the intermediate aerodisk.…”

Section: Geometrymentioning

confidence: 99%

“…This reduces the level of the surface pressure and hence a reduction in drag coefficient in obtained. Recently, Yadav et al [15][16] using computational studies reported an even further increase in the amount of drag reduction at hypersonic flow by mounting a series of aerodisk along the spike stem in comparison to a single aerodisk mounted spiked body configuration. In addition to the spiked blunt bodies, numerous studies have also been conducted involving the investigation of the aerodynamic forces over more streamlined bodies (Cone and Ogive) without mounting any spike [17][18][19].…”

Section: Introductionmentioning

confidence: 99%

“…The flowfield obtained around the hemispherical body by mounting a sharp tip spike of critical spike length is compared with the one ob- tained by mounting a spike of length longer than the critical limit. Furthermore, an attempt is made to increase the percentage of drag reduction on a spike length beyond the critical limit by utilizing the information provided by Jones [4] and Yadav et al [15][16].…”

Section: Introductionmentioning

confidence: 99%

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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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“…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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Aerothermodynamics of generic re-entry vehicle with a series of aerospikes at nose

Cited by 54 publications

References 21 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

Hypersonic Flow over Hemispherical Blunt Body with Spikes

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