Effect of spike on steady and unsteady flow over a blunt body at supersonic speed

Sahoo, Devabrata; Das, Subhajyoti; Kumar, Priyank; Prasad, J. K.

doi:10.1016/j.actaastro.2016.08.005

Cited by 45 publications

(22 citation statements)

References 33 publications

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“…Jagadeesh et al [8] concluded from their numerical and experimental investigations that there was retardation in the flow separations at hypersonic Mach numbers, which in turn resulted in an increased pressure within the separation bubble. An increase in the amplitude of pressure fluctuations was observed for a particular type of spike, with increase in its spike length by Sahoo et al [9]. In addition to it, a reduction in the fluctuations was also seen when the spike shape changed from sharp to blunt to aerospike for a particular spike length.…”

Section: Introductionmentioning

confidence: 82%

Effect on the drag coefficient of various spiked cylinders during buzz phenomenon subjected to hypersonic flows

Rajesh

Rakesh

2020

J Braz. Soc. Mech. Sci. Eng.

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Pulsation mode of transient flow behavior may occur in a violent manner in case of spiked cylinders depending on the geometry, type of spikes, and free stream conditions. Drastic pressure fluctuations near the face of the afterbody have been observed in most cases of pulsating flow mode and thus resulting in drastic variations in the coefficient of drag of the spiked body. The transient analysis of variations in C d with spike length for various spiked cylinders have been carried out in the current work. The variations in C d during one complete cycle as well as variations in time-averaged value of C d with increase in L/D ratios have been analyzed. These variations have been explained with respect to the localized pressure fluctuations, shift in foreshock-aftershock interaction region, effect of effective shielding, and increasing spike lengths. It was found that aerodisk spiked cylinder had the least time-averaged C d. The C d for various other spiked bodies has also been summarized over a range of feasible spike lengths and an optimum design of the spiked body in terms of the spike shape and L/D has also been suggested.

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Section: Introductionmentioning

confidence: 82%

Effect on the drag coefficient of various spiked cylinders during buzz phenomenon subjected to hypersonic flows

Rajesh

Rakesh

2020

J Braz. Soc. Mech. Sci. Eng.

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“…Adding an aerodisk was proved to enhance flow stability associated with mechanical spike devices [63]. Even without using an aerodisk, modifying the tip of a plain spike was proved to have a strong impact on its performance [64] and can reduce flow instability [65,66]. It is also confirmed that the forebody configuration impacts the device effectiveness [33,55,67,68].…”

Section: Factors Controlling the Mechanical Spike Effectiveness And Fmentioning

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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“…The computations have been conducted adopting explicit coupled solver and using "k-ω" turbulence model. The use of this turbulence model has been decided by referring to the turbulence modeling exercise performed by Sahoo et al [8] which reported "k-ω" turbulence model to be suitable for flow analysis over spiked bodies. A typical domain and mesh was finalized after making essential grid sensitivity tests, and obtaining a good match with the results reported in literature which is reported in the subsequent solver validation section.…”

Section: Geometrymentioning

confidence: 99%

“…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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Effect of spike on steady and unsteady flow over a blunt body at supersonic speed

Cited by 45 publications

References 33 publications

Effect on the drag coefficient of various spiked cylinders during buzz phenomenon subjected to hypersonic flows

Effect on the drag coefficient of various spiked cylinders during buzz phenomenon subjected to hypersonic flows

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

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