Assessment of Aerodynamic Effectiveness for Aerospike Application on Hypothesized Lifting Body Configuration in Hypersonic Flow

Khurana, Shashank; Suzuki, Kojiro

doi:10.2514/6.2013-2513

Cited by 6 publications

(5 citation statements)

References 2 publications

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“…The maximum SSO distance occurs for θ = π, hence: ) 1.222 (7) The variation in SSO distance with Fr is shown in Figure 8-10 for the half-wedge angle of 25˚, 30˚, and 37.5˚ respectively. It is clear from Figure 8-10 that with increasing Fr the SSO distance increases.…”

Section: Sso Distance Measurementmentioning

confidence: 99%

“…Some ideas/modifications are implemented by various scientists to alter the fluid flow near the aerodynamic shapes by using passive control and active control devices. Use of spikes is the best example of passive control as it changes a strong shock into a weak foreshock [6,7].…”

Section: Introductionmentioning

confidence: 99%

“…Rathakrishnan and his team reported many studies carried using water channel experiment for visualization of flow over a blunt body, flat plate, and blunt body with a spike. Vortex shedding, shock wave analysis, and pressure uphill movements were thoroughly analyzed [6,7,[21][22][23], and several other [24][25][26]. Thus it is clear from these studies that SSO distance measurement over a wedge is not carried out.…”

Section: Introductionmentioning

confidence: 99%

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Determination of Shock Standoff Distance for Wedge at Supersonic Flow

Mishra

Khan

Mazlan

2019

IJE

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A B S T R A C TAn experimental investigation is conducted to calculate the shock standoff (SSO) distance in front of an acute-angled wedge. For this experimentation, simple water flows channel analysis is carried out. The flow velocity is varied from 13.2 cm/s to 25.5 cm/s increasing in steps of 1 cm/s. A velocity of 13.2 cm/s corresponds to Froude number 1.13 and velocity of 25.5 cm/s to Froude number 1.41. The Froude number ranged from 1.13 to 1.41 in steps of 0.04. The study is conducted on 5 mm thick acrylic sheets and of wedge angles 50°, 60°, and 75° to obtain a relation for calculating the SSO distance concerning the Froude number. It is found that the pressure uphill strongly depends upon the Fr and wedge angle. The SSO distance determined experimentally and using the proposed correlation are found to be in good agreement.

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Section: Sso Distance Measurementmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Determination of Shock Standoff Distance for Wedge at Supersonic Flow

Mishra

Khan

Mazlan

2019

IJE

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“…They used experimental techniques and a simplified model of the resulting basic symmetric-delta configuration. A similar study by the same authors [27] was carried out to assess the aerodynamic efficacy for aerospike on a hypothetical lifting-body in a hypersonic flow at various Mach numbers. In Ref.…”

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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“…Real flight altitudes of supersonic and hypersonic vehicles were also addressed in the literature [119]. Various forebody configurations were examined including models for reentry vehicles [51,55], lifting bodies [29,52,87,120], and complete projectile configurations [121,122]. Design optimization of complete spiked forebody was also performed at different freestream conditions [62,69].…”

Section: Prospective Gaps In the Field Of 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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Assessment of Aerodynamic Effectiveness for Aerospike Application on Hypothesized Lifting Body Configuration in Hypersonic Flow

Cited by 6 publications

References 2 publications

Determination of Shock Standoff Distance for Wedge at Supersonic Flow

Determination of Shock Standoff Distance for Wedge at Supersonic Flow

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

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

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