Flow field behavior with Reynolds number variance around a spiked body

Khurana, Shashank; Suzuki, Kojiro; Rathakrishnan, E.

doi:10.1142/s0217984916503620

Cited by 10 publications

(7 citation statements)

References 2 publications

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“…Re 2700 may be considered as a transition of the flow phenomena for the conical spike, below which it can be considered effective in reducing the pressure height. The spike with hemispherical nose has a larger H/D, which remains constant over the entire experiment range of Re 23 , hence proving that as drag increases Re decreases.…”

Section: Effect Of Reynolds Number On Dragmentioning

confidence: 71%

Higher-Fidelity CFD Tools for Conceptual Design of Supersonic Business Jets

et al. 2022

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Supersonic business jets are regarded as prime modes of next-generation supersonic transport. They allow long-distance travel at low duration by crossing the Mach 1 speed. This results in the breaking of the sound barrier and a sonic boom generated. Sonic boom and aerodynamic efficiency are the biggest concerns for the return of civil supersonic transport. Supersonic vehicles, such as spacecraft, high-speed missiles, and supersonic jets, are subjected to heavy shock wave drag during flight, which will seriously affect the aerodynamic performance of supersonic vehicles. In addition, supersonic vehicles are also subjected to heavy aerodynamic heating during flight. Therefore, modified geometries using aerospikes and aerodisks can be effective to reduce the above-said concerns. In this paper, we discuss aerospikes and aerodisks, its effectiveness, and its importance. The use of these novel mechanisms in the design of supersonic business jets is probed in order to perform future design studies.

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Section: Effect Of Reynolds Number On Dragmentioning

confidence: 71%

Higher-Fidelity CFD Tools for Conceptual Design of Supersonic Business Jets

et al. 2022

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“…In Ref. [28], the experimental research was carried out to determine the importance of the pressure hill height and the zone expansion impact for a flow-through in different forms of spikes with Reynolds numbers ranging from 2278 to 4405 to detect the vortex shedding process. In a prior work, the previous researchers [29] studied a theoretical estimate of the shock standoff distance in a supersonic range with the modified Newtonian impact theory.…”

Section: Flow Controlmentioning

confidence: 99%

A Critical Review of Supersonic Flow Control for High-Speed Applications

2021

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In high-speed fluid dynamics, base pressure controls find many engineering applications, such as in the automobile and defense industries. Several studies have been reported on flow control with sudden expansion duct. Passive control was found to be more beneficial in the last four decades and is used in devices such as cavities, ribs, aerospikes, etc., but these need additional control mechanics and objects to control the flow. Therefore, in the last two decades, the active control method has been used via a microjet controller at the base region of the suddenly expanded duct of the convergent–divergent (CD) nozzle to control the flow, which was found to be a cost-efficient and energy-saving method. Hence, in this paper, a systemic literature review is conducted to investigate the research gap by reviewing the exhaustive work on the active control of high-speed aerodynamic flows from the nozzle as the major focus. Additionally, a basic idea about the nozzle and its configuration is discussed, and the passive control method for the control of flow, jet and noise are represented in order to investigate the existing contributions in supersonic speed applications. A critical review of the last two decades considering the challenges and limitations in this field is expressed. As a contribution, some major and minor gaps are introduced, and we plot the research trends in this field. As a result, this review can serve as guidance and an opportunity for scholars who want to use an active control approach via microjets for supersonic flow problems.

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“…Thus wave losses across a high-pressure along a single normal shock is replaced by pressure distribution along oblique and normal shock [11]. Research shows different types of spikes such as hemisphere spike, conical spike, flat spike, and square spike used to control wave drag and the wake-region behind the fore body is directly influenced by the pressure on its nose and the deflection of the flow [12]. However, all the previous studies focused on controlling high pressure drag using aerospace but no literature to the author's knowledge about base drag reduction with spikes was available.…”

Section: Literature Review Previous Study About Aerospikementioning

confidence: 99%

Flow Control with Aerospike behind Bluff Body

Khan¹,

Tjprc²

2018

IJMPERD

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Flow control in high-speed is challenging due to the high-pressure shock and low-pressure recirculation bubble attached around the vehicle. Wave drag, and Base drag are important accouterments of flow around high-speed objects. This paper deals with base drag, only and presents an experimental study of aerospikes behind the base of bluff bodies to control this drag. A plate of 1 mm thickness with two spikes at 11.5 mm is placed between the nozzle and duct as a passive controller. The Mach numbers deployed for the subsonic regime were 0.6, 0.7 and for transonic regime were 0.8, 0.9 for area ratio 6.25. The L/W ratio taken were 4W, 6W, 8W and 10W. Aerospikes were found to be very effective in controlling base pressure in the transonic regime without influencing the main flow field.

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Flow field behavior with Reynolds number variance around a spiked body

Cited by 10 publications

References 2 publications

Higher-Fidelity CFD Tools for Conceptual Design of Supersonic Business Jets

Higher-Fidelity CFD Tools for Conceptual Design of Supersonic Business Jets

A Critical Review of Supersonic Flow Control for High-Speed Applications

Flow Control with Aerospike behind Bluff Body

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