Investigating incipient separation for an aerofoil at an arbitrary orientation subjected to on oncoming gust: 33rd Scottish Fluid Mechanics Meeting

George Greenlee; Mohammad Koshuriyan; Rohella Muhel

Investigating incipient separation for an aerofoil at an arbitrary orientation subjected to on oncoming gust: 33rd Scottish Fluid Mechanics Meeting

George Greenlee, Mohammad Koshuriyan, Rohella Muhel

Research output: Contribution to conference › Paper

Abstract

The purpose of this paper is to develop an efficient method for analysing the gust response of an aerofoil using CFD. The new method was then applied to investigate how varying the characteristics of a sinusoidal gust affects flow separation over a NACA0012 aerofoil. A two-dimensional periodic gust was implemented in ANSYS Fluent using the User-Defined Function tool. A specialised mesh was designed to allow for accurate modelling of a gust past a NACA0012 aerofoil. The features a rounded trailing edge and an O-grid structure with 164,000 cells. An incompressible SIMPLE pressure-based solver was used in ANSYS Fluent. The k-ωSST turbulence with low Reynold’s corrections was chosen due to its effectiveness in modelling pressure-induced flow separation. The velocity-inlet boundary was defined by the user-defined function velocity components with an angle of attack, α.

Original language	English
Publication status	Published - 28 May 2020
Event	Scottish Fluid Mechanics Meeting - Virtual, Edinburgh, United Kingdom Duration: 28 May 2020 → 28 May 2020 https://sfmm2020.hw.ac.uk/

Conference

Conference	Scottish Fluid Mechanics Meeting
Abbreviated title	33rd SFMM
Country/Territory	United Kingdom
City	Edinburgh
Period	28/05/20 → 28/05/20
Internet address	https://sfmm2020.hw.ac.uk/

Keywords

rapid-distortion theory
leading-edge scattering
receptivity
RDT
sinusoidal gusts
flow separation

Access to Document

https://sfmm2020.hw.ac.uk/wp-content/uploads/Greenlee_George_SFMM202_Abstract.pdf

Cite this

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title = "Investigating incipient separation for an aerofoil at an arbitrary orientation subjected to on oncoming gust: 33rd Scottish Fluid Mechanics Meeting",

abstract = "The purpose of this paper is to develop an efficient method for analysing the gust response of an aerofoil using CFD. The new method was then applied to investigate how varying the characteristics of a sinusoidal gust affects flow separation over a NACA0012 aerofoil. A two-dimensional periodic gust was implemented in ANSYS Fluent using the User-Defined Function tool. A specialised mesh was designed to allow for accurate modelling of a gust past a NACA0012 aerofoil. The features a rounded trailing edge and an O-grid structure with 164,000 cells. An incompressible SIMPLE pressure-based solver was used in ANSYS Fluent. The k-ωSST turbulence with low Reynold{\textquoteright}s corrections was chosen due to its effectiveness in modelling pressure-induced flow separation. The velocity-inlet boundary was defined by the user-defined function velocity components with an angle of attack, α.",

keywords = "rapid-distortion theory, leading-edge scattering, receptivity, RDT, sinusoidal gusts, flow separation",

author = "George Greenlee and Mohammad Koshuriyan and Rohella Muhel",

year = "2020",

month = may,

day = "28",

language = "English",

note = "Scottish Fluid Mechanics Meeting, 33rd SFMM ; Conference date: 28-05-2020 Through 28-05-2020",

url = "https://sfmm2020.hw.ac.uk/",

}

Greenlee, G, Koshuriyan, M & Muhel, R 2020, 'Investigating incipient separation for an aerofoil at an arbitrary orientation subjected to on oncoming gust: 33rd Scottish Fluid Mechanics Meeting', Paper presented at Scottish Fluid Mechanics Meeting, Edinburgh, United Kingdom, 28/05/20 - 28/05/20. <https://sfmm2020.hw.ac.uk/wp-content/uploads/Greenlee_George_SFMM202_Abstract.pdf>

TY - CONF

T1 - Investigating incipient separation for an aerofoil at an arbitrary orientation subjected to on oncoming gust

T2 - Scottish Fluid Mechanics Meeting

AU - Greenlee, George

AU - Koshuriyan, Mohammad

AU - Muhel, Rohella

PY - 2020/5/28

Y1 - 2020/5/28

N2 - The purpose of this paper is to develop an efficient method for analysing the gust response of an aerofoil using CFD. The new method was then applied to investigate how varying the characteristics of a sinusoidal gust affects flow separation over a NACA0012 aerofoil. A two-dimensional periodic gust was implemented in ANSYS Fluent using the User-Defined Function tool. A specialised mesh was designed to allow for accurate modelling of a gust past a NACA0012 aerofoil. The features a rounded trailing edge and an O-grid structure with 164,000 cells. An incompressible SIMPLE pressure-based solver was used in ANSYS Fluent. The k-ωSST turbulence with low Reynold’s corrections was chosen due to its effectiveness in modelling pressure-induced flow separation. The velocity-inlet boundary was defined by the user-defined function velocity components with an angle of attack, α.

AB - The purpose of this paper is to develop an efficient method for analysing the gust response of an aerofoil using CFD. The new method was then applied to investigate how varying the characteristics of a sinusoidal gust affects flow separation over a NACA0012 aerofoil. A two-dimensional periodic gust was implemented in ANSYS Fluent using the User-Defined Function tool. A specialised mesh was designed to allow for accurate modelling of a gust past a NACA0012 aerofoil. The features a rounded trailing edge and an O-grid structure with 164,000 cells. An incompressible SIMPLE pressure-based solver was used in ANSYS Fluent. The k-ωSST turbulence with low Reynold’s corrections was chosen due to its effectiveness in modelling pressure-induced flow separation. The velocity-inlet boundary was defined by the user-defined function velocity components with an angle of attack, α.

KW - rapid-distortion theory

KW - leading-edge scattering

KW - receptivity

KW - RDT

KW - sinusoidal gusts

KW - flow separation

M3 - Paper

Y2 - 28 May 2020 through 28 May 2020

ER -