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Dissertations / Theses on the topic 'Aerofoil'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Kingan, Michael Joseph. "Aeroacoustic noise produced by an aerofoil." Thesis, University of Canterbury. Mechanical Engineering, 2005. http://hdl.handle.net/10092/6596.

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This thesis describes an investigation into the aeroacoustic noise produced by an aerofoil using experimental, computational and theoretical methods. Several different types of aeroacoustic noise generation mechanisms and the parameters which affect these mechanisms were identified and investigated. The aerofoils used' in this investigation all had chord lengths of 100mm and had a maximum thickness between 18mm and 30mm. Experimental testing was undertaken in the low noise wind tunnel in the Department of Mechanical Engineering at the University of Canterbury with the aerofoils mounted at the

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2

Andrew, David Neil. "Flow in regenerative compressors with aerofoil blading." Thesis, University of Cambridge, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.235767.

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Regenerative compressors are low specific speed, tangential flow turbomachines in which the working fluid follows an approximately toroidal-helical path around the machine. Although regenerative turbomachines have been in use for over fifty years, the use of aerofoil blades (as opposed to the more usual straight vanes) is a relatively new innovation designed to improve the internal flow. However, little work has been done on the details of this flow. This dissertation concentrates on the flow in the main region of the compressor, away from the inlet and exit ports. A simple, analytical model o

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3

Khoo, Hilary. "Separated flow past wind turbine aerofoil sections." Thesis, Imperial College London, 1991. http://hdl.handle.net/10044/1/46866.

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4

Paruchuri, Chaitanya. "Aerofoil geometry effects on turbulence interaction noise." Thesis, University of Southampton, 2017. https://eprints.soton.ac.uk/415884/.

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Fan broadband is one of the dominant noise sources on an aircraft engine, particularly at approach. The dominant noise generation mechanism is due to turbulent- aerofoil interaction noise (TAI). This thesis investigates the effect of changes in 2D aerofoil geometry on TAI noise. The main focus of this thesis is to attempt to reduce it through the development of innovative leading edge geometries. The ﬁrst two chapters of the thesis deals with an experimental and numerical investigation into the effect of aerofoil geometry on interaction noise on single aerofoils and on cascades. Consistent wit

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5

Crompton, Matthew John. "The thin aerofoil leading edge separation bubble." Thesis, University of Bristol, 2001. http://hdl.handle.net/1983/25312c88-4d89-4149-bee9-d56cf80d9735.

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6

Chew, Siou Chye. "Numerical simulations of oscillatory flapping aerofoil propulsion." Thesis, Imperial College London, 2011. http://hdl.handle.net/10044/1/8137.

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The primary objective of the current research is to develop a Computational Fluid Dynamics (CFD) model to investigate rigid and flexible aerofoil propulsive characteristics when the aerofoil IS subjected to oscillatory flapping motions. The study is also extended to rectangular wings. Flows past the flapping aero foils at moderate Reynolds numbers are simulated using the twodimensional incompressible Navier-Stokes equations. The Baldwin-Lomax algebraic turbulence model is incorporated to determine eddy viscosity for higher Reynolds numbers turbulent flow simulations. Flows past flapping wings

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7

Hustad, C. W. "The drag of a circulation controlled aerofoil." Thesis, University of Bath, 1986. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.370668.

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8

Phillips, Russell Leslie. "Development of a reciprocating aerofoil wind energy harvester." Thesis, Nelson Mandela Metropolitan University, 2008. http://hdl.handle.net/10948/899.

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Cross flow wind turbines are not unique. The performance of Savonius and Darrieus turbines is well documented. Both share the advantage of being able to accept fluid flow from any direction. The Savonius is drag based and hence has poor power output while the Darrieus is lift based. Due to the fact that the Darrieus has fixed blades the fluid flow through the rotor does not result in optimal lift being generated at all points in the rotation circle. A drawback of the Darrieus system is that it has to operate at a high tip-to wind-speed ratio to obtain reasonable performance with the fixed blad

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9

Gorman, J. "Vortex formation in the flow around a lifting aerofoil." Thesis, Swansea University, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.637079.

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This thesis presents an investigation of vortex formation in the flow around a lifting aerofoil both with and without acoustic forcing. The chord Reynolds number range covered is from 3000 to 300000. At low chord Reynolds number, (3000 to 20000), and low incidence, (0 to 8°), vortex formation in the flow around an aerofoil has been studied in a water tunnel. Stability theory and in particular the concepts of absolute and convective instability are applied to the aerofoil wake. It is found that for non zero incidence a region of absolutely unstable flow is associated with the separation bubble.

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10

Baker, David. "Design of a morphing aerofoil using compliant structure optimisation." Thesis, University of Bristol, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.529826.

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11

Ho, Pui Yin. "An interactive boundary layer method for subsonic aerofoil flows." Thesis, Imperial College London, 1989. http://hdl.handle.net/10044/1/47475.

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12

Fernie, Robert Mark. "Low frequency shock motion on a NACA 0012 aerofoil." Thesis, University of Cambridge, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.614936.

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13

Pope, Martin Peter. "Mathematical modelling of unsteady problems in thin aerofoil theory." Thesis, University of Southampton, 1999. https://eprints.soton.ac.uk/192771/.

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The de-icing of aircraft wings by the injection of fluid through a slot in the leading edge of the wing is analysed. A review of current de-icing methods is presented and the semi-infinite slot-injection equation derived, which is a singular partial integro-differential equation. The Stefan condition is used to close the system. A discretisation of the equation is presented and the subsequent numerical results are analysed. The model is then revised to account for the retraction of the ice layer away from the slot. An asymptotic result for the thin ice layers is also presented. The problem of

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14

Ai, Qing. "Novel morphing structures for aerofoil flow and noise control purposes." Thesis, University of Bristol, 2016. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.720818.

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15

Lattimer, Timothy Richard Bislig. "Singular partial integro-differential equations arising in thin aerofoil theory." Thesis, University of Southampton, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.243192.

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16

Lewis, Mark Charles. "Aerofoil testing in a self-streamlining flexible walled wind tunnel." Thesis, University of Southampton, 1987. https://eprints.soton.ac.uk/52285/.

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17

Morin, Sandrine. "A combined numerical and experimental study of aerofoil separation bubbles." Thesis, University of Southampton, 2003. https://eprints.soton.ac.uk/47094/.

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18

Ou, Hengan. "Finite element analysis and experimental investigation of stiffness characteristics of forming presses and forging of turbine aerofoil components." Thesis, University of Strathclyde, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.366750.

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19

Gibson, Thomas Mark. "The passive control of shock-wave/boundary-layer interactions." Thesis, University of Cambridge, 1997. https://www.repository.cam.ac.uk/handle/1810/272691.

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20

Cameron, Lee Stewart William. "Adaptive multi-objective aerofoil optimisation : impact of surface contamination and degradation." Thesis, Queen's University Belfast, 2013. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.602451.

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The preliminary design of aerofoils for use in versatile air vehicles is considered, with a view to addressing the sensitivity of the boundary layer transition to surface imperfections arising through surface contamination and degradation. An efficient multi-objective optimisation framework has been developed, enabling optimal trade-offs between key flight conditions to be quantified which include the impact of surface contaminants on the evolution of the design space. The impact of surface contamination and degradation on the design of optimal profiles is assessed through the reduction in the

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21

Andreou, Christodoulos. "Acoustic and aerodynamic properties of aerofoil leading-edge high-lift geometries." Thesis, University of Cambridge, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.611404.

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22

Lu, Bin. "3D Die Shape Optimisation For Net Shape Forging of Aerofoil Blades." Thesis, Queen's University Belfast, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.501609.

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23

McAlpine, Alan. "Generation of discrete frequency tones by the flow around an aerofoil." Thesis, University of Bristol, 1997. http://hdl.handle.net/1983/cbeb5264-28b8-4d23-b7bf-e869ea55a4a8.

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Tonal noise, the self-induced discrete frequency noise generated by aerofoils, is investigated. It is heard from an aerofoil placed in streams at low Mach number flows when inclined at a small angle to the stream. The tones are heard as a piercing whistle, commonly up to 30 dB above the background noise level. The work is motivated by the occurrence of tonal noise from rotors, fans and recently wind-turbines. Previous authors have attributed tonal noise to a feedback loop consisting of a coupling between laminar boundary-layer instability waves and sound waves propagating in the free stream. T

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24

Huang, X. "Active control of aerodynamic instabilities." Thesis, University of Cambridge, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.237877.

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25

Cyr, Stéphane. "A theoretical model for flow about a circular-arc aerofoil with separation /." Thesis, McGill University, 1992. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=61186.

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The aim of the present research is to develop a theoretical model that could predict the trailing-edge separation over a circular-arc aerofoil and its effect on the pressure distribution, and on the lift. The model uses sources, in a potential flow, to simulate the effect of the separated region on the pressure distribution. An integral method, turbulent boundary-layer development, combined with the irrotational pressure distribution on the circular-arc predicts the point of separation. To make sure that trailing-edge separation is present alone and mostly to avoid any difficulties in predicti

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26

Fox, M. D. "A study of bond coat cracking in TBCs for turbine aerofoil applications." Thesis, University of Cambridge, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.599161.

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This dissertation describes work on the thermomechanical fatigue (TMF) behaviour of coated single crystal, nickel-based superalloys. During the course of study, the TMF facility at Cambridge was developed to enhance the reliability of the test technique and to enable the testing of thin ceramic shell TBC test pieces. Benchmark TMF tests were carried out under strain control on a series of different coatings to evaluate the performance of two new coat systems developed at Rolls-Royce that incorporate a platinum surface modification. Cyclic life to failure suggested that the surface modification

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27

Tattersall, P. "Evaluation and reduction of numerical diffusion effects in viscous aerofoil flow calculations." Thesis, Loughborough University, 1993. https://dspace.lboro.ac.uk/2134/6755.

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The Reynolds-averaged Navier-Stokes (RANS) equations form the most accurate model of viscous flow which can currently be solved computationally on a routine basis for practical engineering problems, given the size and cost of present-day computers. Before RANS solution methods can be used with confidence for the design of aircraft components, a number of areas related to solution accuracy must be investigated, one of which is numerical diffusion. Numerical diffusion, arising from the discrete solution method employed, is necessary to ensure numerical stability, but if too much is included the

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28

Mitchell, Robert David. "A computational study of heat transfer on transonic flow over an aerofoil." Thesis, Queen's University Belfast, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.238992.

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29

Obiga, Otuami. "Investigation of the performance of a slotted aerofoil at low Reynolds numbers." Thesis, University of Nottingham, 2018. http://eprints.nottingham.ac.uk/46841/.

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Slotted aerofoils have been suggested by numerous researchers as an effective means of controlling boundary layer flow separation, and improving aerodynamic performance. Numerous slot designs have been studied at high Reynolds number, but there is scarcity of study of such slots effect on aerofoil performance in low Reynolds number scenarios. In the present work, wind tunnel and numerical investigation of the effect of a unique slot configuration and its geometric parameters on the aerodynamic performance of a NACA0018 aerofoil at low Reynolds number was executed. The aim of this work is to as

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30

Margot, Xandra Marcelle. "A physically guided zonal approach for Euler/Navier-Stokes predictions of aerofoil flows." Thesis, Imperial College London, 1993. http://hdl.handle.net/10044/1/11469.

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31

Adair, Desmond. "Turbulent flow in the vicinity of the trailing-edge of an aerofoil flap." Thesis, Imperial College London, 1986. http://hdl.handle.net/10044/1/37915.

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32

Breitfeld, Oliver. "Improving the performance of aerofoil sections using momentum transfer via a secondary flow." Thesis, University of South Wales, 2002. https://pure.southwales.ac.uk/en/studentthesis/improving-the-performance-of-aerofoil-sections-using-momentum-transfer-via-a-secondary-flow(a3627a17-2b56-4e3a-9c73-64e0e105f3d6).html.

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Aerodynamic flow control can improve aerofoil performance by influencing the natural growth of boundary layers, which develop on the surface of vehicles moving in viscous fluids. Many active and passive techniques have been developed to reduce drag and/or increase the lift of aerofoil sections. The work presented in this thesis is concerned with the active excitation of the boundary layer on the suction side of aerofoil sections through momentum transfer via a secondary flow. The secondary flow was achieved by air passing through an air breathing device (ABD) which was implemented in the aerof

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33

De, Silva R. Suraj I. "The flow field induced by a flat plate aerofoil with simulated battle damage." Thesis, Loughborough University, 2009. https://dspace.lboro.ac.uk/2134/34300.

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This investigation looks into the induced surface pressure field and flow field of a 2-D flat plate aerofoil with simulated battle damage. Enhancing survivability is a major design criteria for military aircraft designers, and the aerodynamic effects of battle damage has recently come to the fore as an area that warrants further attention. The current investigation is in effect a continuation of the battle damage research initiated at Loughborough University by Irwin, with the ultimate aim of enabling quick and accurate CFD studies to assess the aerodynamic impact of battle damage on a lifting

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34

Rosti, Marco. "Direct numerical simulation of an aerofoil at high angle of attack and its control." Thesis, City, University of London, 2016. http://openaccess.city.ac.uk/15843/.

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Detailed analysis of the flow around a NACA0020 aerofoil at moderate low chord Reynolds number (Rec = 2×104) in completely stalled conditions has been carried out by means of Direct Numerical Simulations. The stalled condition is either a steady configuration at a fixed angle of attack (α = 20o) or it is reached via a ramp-up manoeuvre, increasing the angle of attack from 0o to 20o. Concerning this last case, new insights on the vorticity dynamics leading to the lift overshoot, lift crisis and the damped oscillatory cycle that gradually matches the steady condition, are discussed using a numbe

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35

Yeung, Matthew. "The sound field due to a pair of vortices moving past a thin aerofoil." Thesis, Imperial College London, 2003. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.404471.

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36

Jones, Gareth. "Control of flow around an aerofoil at low Reynolds numbers using periodic surface morphing." Thesis, Imperial College London, 2016. http://hdl.handle.net/10044/1/51101.

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This thesis combines experimental and computational methods to investigate the low Reynolds number flow (Re = 50,000) around a NACA 4415 aerofoil, and its control using periodic surface motion. A physical model was fabricated and tested in a closed-loop wind tunnel and a good comparison between the experiments and computations was achieved. Time-resolved measurements of the surface reveal that the peak-to-peak displacement is a function of both the amplitude and frequency of the input voltage signal but the addition of aerodynamic forces does not cause significant changes in surface behaviour.

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37

Song, Longfei. "Leading-edge flow separation control over a NACA 0012 aerofoil with DBD plasma actuators." Thesis, University of Nottingham, 2018. http://eprints.nottingham.ac.uk/49841/.

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An experimental investigation has been conducted in a low-speed wind tunnel at the University of Nottingham to study the flow separation control capability of a wall-normal plasma jet by DBD plasma actuator over a NACA 0012 aerofoil. As an active flow separation control technique, DBD plasma actuators could be applied when required to manipulate a flow. They are surface-mounted and require no moving parts, ducts, holes or cavities, so no profile drag penalty will be caused. Moreover, they are fast responding since they are purely electrical devices and could be operated at a higher frequency r

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38

Kadja, M. "Computation of recirculating flow in complex domains with algebraic Reynolds stress closure and body fitted meshes." Thesis, University of Manchester, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.384419.

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39

Greene, Robert Matthew. "Finite element simulation and die shape optimisation method applied to forging of 3D aerofoil blades." Thesis, Queen's University Belfast, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.485072.

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The dimensional tolerances are among the most important manufacturing criteria in the forging of aerofoil blades for aero-engine applications. These are usually classified in relation to aerofoil shape, thickness and twist along cross-sections and are. affected by many factors such as preform shape, temperature, die elasticity and component springback. The interaction of all these factors makes design for net-shape forging extremely difficult. The focus was on the final shape of the forged aerofoil blades, which was affected by temperature, die elasticity and springback. A thermaIly coupled 3D

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40

Makem, J. E. "Virtual Net-Shape Forging of Aerofoil Blades - Dimensional Inspection and Shape Sensitivity to Process Variables." Thesis, Queen's University Belfast, 2010. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.517543.

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41

Lau, Alex Siu Hong. "High-order computations on aerofoil-gust interaction noise and the effects of wavy leading edges." Thesis, University of Southampton, 2012. https://eprints.soton.ac.uk/355961/.

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High-order accurate numerical simulations are performed to investigate the effects of wavy leading edges on aerofoil gust interaction (AGI) noise. The present study is based on periodic velocity dis-turbances predominantly in streamwise (x-) and vertical (y-) directions that are mainly responsible for the surface pressure fluctuation of an aerofoil. The perturbed velocity components of the present gust model do not vary in the spanwise (z-) direction. In general, the present results show that wavy leading edges lead to reduced AGI noise. Under the current incident gusts, it is found that the r

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42

Tsiachris, Fotios K. "Retreating blade stall control on a NACA 0015 aerofoil by means of a trailing edge flap." Thesis, University of Glasgow, 2005. http://theses.gla.ac.uk/5109/.

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Trailing edge flaps may provide a mechanism for alleviating retreating blade stall. In the present investigation numerical simulations were conducted involving a NACA 0015 aerofoil section fitted with a plain trailing edge (TE) flap. All simulations were conducted using DIVEX, a tool being developed at the University of Glasgow, Department of Aerospace Engineering. In summary, the code uses a surface shedding discrete vortex method (DVM) for the simulation of 2-D incompressible flows around pitching aerofoils. The aero-foil is oscillating in pitch about its quarter chord axis and the clap unde

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43

Lewington, Neil. "Enhancing lift on a three element high lift aerofoil system by installing air jet vortex generators." Thesis, City University London, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.269315.

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44

Powell, Jonathan Edward. "The application of particle image velocimetry to vortical flow fields." Thesis, Heriot-Watt University, 2000. http://hdl.handle.net/10399/575.

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45

Walter, Daniel James, and Daniel james walter@gmail com. "Study of aerofoils at high angle of attack in ground effect." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080110.145138.

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Aerodynamic devices, such as wings, are used in higher levels of motorsport (Formula-1 etc.) to increase the contact force between the road and tyres (i.e. to generate downforce). This in turn increases the performance envelope of the race car. However the extra downforce increases aerodynamic drag which (apart from when braking) is generally detrimental to lap-times. The drag acts to slow the vehicle, and hinders the effect of available drive power and reduces fuel economy. Wings, in automotive use, are not constrained by the same parameters as aircraft, and thus higher angles of attack can b

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46

Gobbi, Giangiacomo. "Analysis and reconstruction of dynamic-stall data from nominally two-dimensional aerofoil tests in two different wind tunnels." Thesis, University of Glasgow, 2010. http://theses.gla.ac.uk/1362/.

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This work is a specific investigation into low speed aerofoils. The term “low speed” is normally used to indicate free stream velocity less than Mach = 0.5 and, here, not more than 0.2 M when considering dynamic-stall. This field of investigation, for the QinetiQ aerofoil, has been somewhat ignored till now to the advantage of higher speeds starting from 0.3 M. In order to improve the knowledge of the behaviour of aerofoils under M<0.2 conditions, the University of Glasgow, in cooperation with QinetiQ, carried out two-dimensional aerodynamic tests on a RAE9645 aerofoil in 2002. By the end of N

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47

Carr, M. I. "The excitation of acoustic resonances in an axial flow compressor stage by vortex shedding from aerofoil section blading." Thesis, Swansea University, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.636209.

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In recent years continuing development of the axial flow compressor for use in the aero-engine has increased its susceptibility to unsteady flow phenomena which can cause severe blade vibration. A source which has emerged and become of considerable importance is excitation by acoustic resonances. An experimental investigation in a single stage axial flow compressor rig has been performed to ascertain whether acoustic resonances can be excited by vortex shedding from loaded aerofoil section blades. A further experimental programme, to study further the effect of inter-row spacing, was peformed

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48

Mulholland, Daniel J. "Distribution of aerofoil section lift from section pitching moment applied to a dynamic model for aircraft poststall departure." Thesis, This resource online, 1995. http://scholar.lib.vt.edu/theses/available/etd-02132009-172236/.

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49

El-Ibrahim, Salah Jamil Saleh. "Prediction of the effects of aerofoil surface irregularities at high subsonic speeds using the Viscous Garabedian and Korn (VKG) method." Thesis, University of Hertfordshire, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.365928.

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50

Irwin, Andrew J. "Investigation into the aerodynamic effects of simulated battle damage to a wing." Thesis, Loughborough University, 1999. https://dspace.lboro.ac.uk/2134/10735.

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A key stage in the design-cycle of a military aircraft is the assessment of its vulnerability to hostile threat mechanisms. Such mechanisms inflict battle-damage to the aircraft structure and systems. This experimental investigation considered the aerodynamic consequences of simulated battle-damage to a two-dimensional wing. Key assumptions and techniques were identified leading to the modelling of both gunfire and missile fragmentation damage. Wind tunnel balance measurements were undertaken, together with surface pressure measurements and flow-visualisation methods. Force and moment results

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