Flow Field around a Blunt-nosed Body with Spike

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

doi:10.1515/tjj-2012-0002

Cited by 8 publications

(6 citation statements)

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“…The flow past desired blunt-nosed body with and without spikes was tested in a primary 2D water channel, at a given Reynolds number [25], with spikes of various forms, such as conical, hemispherical, flat, and square nose. Khurana and Suzuki [26] used a forward-facing aerospike on the nose to examine the heat transfer and its control through the aerospikes for lifting the body configuration in a hypersonic flow.…”

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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Section: Flow Controlmentioning

confidence: 99%

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

2021

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“…It was seen that the flow turned oscillatory when η and α were regulated separately for both with and without control. Several other experimental research works were carried out by using an active/passive control system to control flow separation [13][14][15][16][17][18]. Furthermore, these experimental works were validated using the computational fluid dynamics (CFD) technique by many researchers.…”

Section: Introductionmentioning

confidence: 99%

Investigation of suddenly expanded flows at subsonic Mach numbers using an artificial neural networks approach

Quadros

Nagpal²,

Khan³

et al. 2022

PLoS ONE

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The purpose of this study is to explore two concepts: first, the use of artificial neural networks (ANN) to forecast the base pressure (β) and wall pressure (ω) originating from a suddenly expanded flow field at subsonic Mach numbers. Second, the implementation of Garson approach to determine the critical operating parameters affecting the suddenly expanded subsonic flow process in the subsonic range. In a MATLAB environment, a network model was constructed based on a multilayer perceptron with an input, hidden, and output layer. The network input parameters were the Mach number (M), nozzle pressure ratio (η), area ratio (α), length to diameter ratio (γ), micro jet control (ϵ), and duct location to length ratio (δ). The network output included two variables; base pressure (β) and wall pressure (ω). The ANN was trained and tested using the experimental data. The experimental results found that micro-jet controls were successful in increasing the base pressure for low Mach numbers and high nozzle pressure ratios. It was also found that the wall pressure was same for with and without micro jet control. The ANN predicted values agreed well with the experimental values, with average relative errors of less than 5.02% for base pressure and 6.71% for wall pressure. Additionally, with a relative significance of 32% and 43%, the nozzle pressure ratio and duct location to length ratio had the highest influence on the base pressure and wall pressure, respectively. The results demonstrate that the ANN model is capable of accurately predicting the pressure results, enabling theoretical foundation for research into pressure distribution in aerodynamic systems.

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“…Here, a geometrical adjustment is made downstream of the nozzle exit that causes variation in base pressure. Khurana et al [11] conducted experiments on the blunt-body by implementing spikes. Spikes of different shapes such as flat, square, and conical were used.…”

Section: Introductionmentioning

confidence: 99%

Machine Learning Applications in Modelling and Analysis of Base Pressure in Suddenly Expanded Flows

et al. 2021

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Base pressure becomes a decisive factor in governing the base drag of aerodynamic vehicles. While several experimental and numerical methods have already been used for base pressure analysis in suddenly expanded flows, their implementation is quite time consuming. Therefore, we must develop a progressive approach to determine base pressure (β). Furthermore, a direct consideration of the influence of flow and geometric parameters cannot be studied by using these methods. This study develops a platform for data-driven analysis of base pressure (β) prediction in suddenly expanded flows, in which the influence of flow and geometric parameters including Mach number (M), nozzle pressure ratio (η), area ratio (α), and length to diameter ratio (φ) have been studied. Three different machine learning (ML) models, namely, artificial neural networks (ANN), support vector machine (SVM), and random forest (RF), have been trained using a large amount of data developed from response equations. The response equations for base pressure (β) were created using the response surface methodology (RSM) approach. The predicted results are compared with the experimental results to validate the proposed platform. The results obtained from this work can be applied in the right way to maximize base pressure in rockets and missiles to minimize base drag.

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Flow Field around a Blunt-nosed Body with Spike

Cited by 8 publications

References 0 publications

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

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

Investigation of suddenly expanded flows at subsonic Mach numbers using an artificial neural networks approach

Machine Learning Applications in Modelling and Analysis of Base Pressure in Suddenly Expanded Flows

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