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Dissertations / Theses on the topic 'Unsteady Airfoil'

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Published: 4 June 2021

Last updated: 5 February 2022

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1

Cricelli, Antonio M. "Unsteady airfoil flow solutions on moving zonal grids." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/23803.

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2

Scott, Matthew Thomas. "Nonlinear airfoil-wake interaction in large amplitude unsteady flow." Thesis, Massachusetts Institute of Technology, 1987. http://hdl.handle.net/1721.1/14650.

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3

Poling, David R. "Airfoil response to periodic disturbances: the unsteady Kutta condition." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/76166.

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Unsteady flow fields over a NACA 0012 at an angle of attack are investigated. The first is the classical pitching motion about the airfoil's quarter chord. The second is the flow over a fixed airfoil immersed in the wake of the pitching airfoil. Large reduced frequencies are considered. Measurements were obtained in a water tunnel by Laser-Doppler velocimetry. Ensemble-averaged velocity measurements were obtained in the vicinity of the trailing edges of both the pitching and the fixed airfoils. The flowfields in the wake and at the trailing edges of both airfoils were studied visually. The val

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4

Yeow, Kim Fong. "An experimental investigation High rate/high lift aerodynamics Unsteady airfoil." Ohio University / OhioLINK, 1989. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1182179063.

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5

Staubs, Joshua Kyle. "Real Airfoil Effects on Leading Edge Noise." Diss., Virginia Tech, 2008. http://hdl.handle.net/10919/27911.

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This dissertation presents measurements of the far-field noise associated with the interaction of grid-generated turbulence with a series of airfoils of various chord lengths, thicknesses, and camber. The radiated noise was measured for a number of angles of attack for each airfoil to determine the effects of angle of attack on the leading edge noise. Measurements are compared with numerous theories to determine the mechanism driving the production of leading edge noise. Calculations were also made using a boundary element method to determine the effects of airfoil shape on the unsteady loadin

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6

Price, Jennifer Lou. "Unsteady Measurements and Computations on an Oscillating Airfoil with Gurney Flaps." NCSU, 2001. http://www.lib.ncsu.edu/theses/available/etd-20010713-170959.

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<p>Price, Jennifer Lou. Unsteady Measurements and Computations on an Oscillating Airfoil with Gurney Flaps. (Under the direction of Dr. Ndaona Chokani)The effect of a Gurney flap on an unsteady airfoil flow is experimentally and computationally examined. In the experiment, the details of the unsteady boundary layer events on the forward portion of the airfoil are measured. In the computation, the features of the global unsteady flow are documented and correlated with the experimental observations.The experiments were conducted in the North Carolina State University subsonic wind tunnel on an o

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7

Durand, Eric 1973. "Time domain modeling of unsteady aerodynamic forces on a flapping airfoil." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/47668.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998.<br>Includes bibliographical references (p. 69-70).<br>The goal of this research is to develop a versatile and fast code to compute the unsteady lift and thrust forces generated by a flapping airfoil and apply it to engineering problems. We consider both plunging and pitching types of motion and develop a time marching simulation based on early work in unsteady aerodynamics. The ability of the code to compute lift and thrust forces is validated against published results. We then study ways to maxi

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8

Kong, Lingzhe. "Experimental investigation of the tolerant wind tunnel for unsteady airfoil motion testing." Thesis, University of British Columbia, 1991. http://hdl.handle.net/2429/29992.

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Previously, the concept of the tolerant wind tunnel, developed in the Department of Mechanical Engineering, U. B. C., was tested only for stationary models. In the present study, the concept is investigated for unsteady airfoil motion. The new wind tunnel test section, using the opposite effects of solid and open boundaries, is a new approach to reduce wall blockage effects. Consisting of vertical airfoil slats uniformly spaced on both side walls in the test section, it is designed to produce a nearly free-air test environment for the test model, which leads to negligible or small corrections

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9

Castañeda, Vergara David Armando. "Active Control of Flow over an Oscillating NACA 0012 Airfoil." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1587420875168203.

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10

Gornowicz, Galen Gerald Dimotakis Paul E. "Continuous-field image-correlation velocimetry and its application to unsteady flow over an airfoil /." Diss., Pasadena, Calif. : California Institute of Technology, 1997. http://resolver.caltech.edu/CaltechETD:etd-08062004-141142.

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11

Webb, Charles. "Separation and Vorticity Transport in Massively-Unsteady Low Reynolds Number Flows." Wright State University / OhioLINK, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=wright1244864717.

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12

Mish, Patrick Francis. "An Experimental Investigation of Unsteady Surface Pressure on Single and Multiple Airfoils." Diss., Virginia Tech, 2003. http://hdl.handle.net/10919/26567.

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This dissertation presents measurements of unsteady surface pressure on airfoils encountering flow disturbances. Analysis of measurements made on an airfoil immersed in turbulence and comparisons with inviscid theory are presented with the goal of determining the effect of angle of attack on an airfoils inviscid response. Unsteady measurements made on the surface of a linear cascade immersed in periodic flow are presented and analyzed to determine the relationship between the blades inviscid response and tip leakage vortex strength. Measurements of fluctuating surface pressure were made o

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13

Young, John Aerospace Civil &amp Mechanical Engineering Australian Defence Force Academy UNSW. "Numerical simulation of the unsteady aerodynamics of flapping airfoils." Awarded by:University of New South Wales - Australian Defence Force Academy. School of Aerospace, Civil and Mechanical Engineering, 2005. http://handle.unsw.edu.au/1959.4/38656.

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There is currently a great deal of interest within the aviation community in the design of small, slow-flying but manoeuvrable uninhabited vehicles for reconnaissance, surveillance, and search and rescue operations in urban environments. Inspired by observation of birds, insects, fish and cetaceans, flapping wings are being actively studied in the hope that they may provide greater propulsive efficiencies than propellers and rotors at low Reynolds numbers for such Micro-Air Vehicles (MAVs). Researchers have posited the Strouhal number (combining flapping frequency, amplitude and forward speed)

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14

Lehr, Andreas Lehr Andreas. "Application of a particle image velocimetry system to the periodic unsteady flow around an isolated compressor airfoil /." [S.l.] : [s.n.], 2002. http://library.epfl.ch/theses/?nr=2557.

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15

Vinci, Samuel J. "CFD SIMULATIONS FOR THE EFFECT OF UNSTEADY WAKES ON THE BOUNDARY LAYER OF A HIGHLY LOADED LOW PRESSURE TURBINE AIRFOIL (L1A)." Cleveland State University / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=csu1307111386.

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16

Mish, Patrick F. "Mean Loading and Turbulence Scale Effects on the Surface Pressure Fluctuations Occurring on a NACA 0015 Airfoil Immersed in Grid Generated Turbulence." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/33751.

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Detailed surface pressure measurements have been made on a NACA 0015 immersed in two grid generated homogenous flows at Re = 1.17 x 10^6 for a = 0Â°, 4Â°, 8Â°, 12Â°, 16Â°, and 20Â°. The goal of this measurement was to reveal and highlight mean loading and turbulence scale effects on surface pressure fluctuations resulting from turbulence/airfoil interaction. Also, measurements are compared with the theory of Amiet (1976a,b). The surface pressure response shows a dependance on angle of attack, the nature of which is related to the relative chord/turbulence scale. The dependance on turbulenc

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17

Ozdemir, Enver Doruk. "Implementation Of Rotation Into A 2-d Euler Solver." Master's thesis, METU, 2005. http://etd.lib.metu.edu.tr/upload/12606525/index.pdf.

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The aim of this study is to simulate the unsteady flow around rotating or oscillating airfoils. This will help to understand the rotor aerodynamics, which is essential in turbines and propellers. In this study, a pre-existing Euler solver with finite volume method that is developed in the Mechanical Engineering Department of Middle East Technical University (METU) is improved. This structured pre-existing code was developed for 2-D internal flows with Lax-Wendroff scheme. The improvement consist of firstly, the generalization of the code to external flow<br>secondly, implementation of fi

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18

Neculita, Catalin Silviu. "Unsteady compressible flows past oscillating airfoils." Thesis, McGill University, 2005. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=99002.

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This thesis presents new and efficient analytical solutions for the unsteady subsonic compressible flows past rigid and flexible airfoils executing low frequency oscillations. These solutions are obtained using an especially developed method based on velocity singularities associated with the airfoil leading edge and ridges, which define the changes in the airfoil boundary conditions. The velocity singularity method has been initially developed by Mateescu.<br>Closed form solutions are presented for the unsteady lift and pitching moment coefficients and for the chordwise distribution of the un

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19

Walker, William Paul. "Unsteady Aerodynamics of Deformable Thin Airfoils." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/34620.

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Unsteady aerodynamic theories are essential in the analysis of bird and insect flight. The study of these types of locomotion is vital in the development of flapping wing aircraft. This paper uses potential flow aerodynamics to extend the unsteady aerodynamic theory of Theodorsen and Garrick (which is restricted to rigid airfoil motion) to deformable thin airfoils. Frequency-domain lift, pitching moment and thrust expressions are derived for an airfoil undergoing harmonic oscillations and deformation in the form of Chebychev polynomials. The results are validated against the time-domain unstea

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20

Cencelli, Nicolette Arnalda, Bakstrom T. W. Von, and T. S. A. Denton. "Aerodynamic optimisation of a small-scale wind turbine blade for low windspeed conditions." Thesis, Stellenbosch : Stellenbosch University, 2006. http://hdl.handle.net/10019.1/353.

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Thesis (MScEng (Department of Mechanical and Mechatronic Engineering))--Stellenbosch University, 2006.<br>ENGLISH ABSTRACT: Wind conditions in South Africa determine the need for a small-scale wind turbine to produce useable power at windspeeds below 7m/s. In this project, a range of windspeeds, within which optimal performance o the wind turbine is expected, was selected. The optimal performance was assessed in terms of the Coefficient of Power(Cp), which rates the turbines blade's ability to extract energy form the avalible wind stream. The optimisation methods employed allowed a means of

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21

Wu, Jiunn-Chi. "A study of unsteady turbulent flow past airfoils." Diss., Georgia Institute of Technology, 1988. http://hdl.handle.net/1853/13091.

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22

Tuncer, Ismail H. "Unsteady aerodynamics of oscillating and rapidly pitched airfoils." Diss., Georgia Institute of Technology, 1988. http://hdl.handle.net/1853/12522.

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23

Kaya, Mustafa. "Path Optimization Of Flapping Airfoils Based On Unsteady Viscous Flow Solutions." Phd thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/2/12609349/index.pdf.

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The flapping path of a single airfoil and dual airfoils in a biplane configuration is optimized for maximum thrust and/or propulsive efficiency. Unsteady, low speed viscous flows are computed using a Navier-Stokes solver in a parallel computing environment. A gradient based algorithm and Response Surface Methodology (RSM) are employed for optimization. The evaluation of gradient vector components and the design of experiments for RSM, which require unsteady solutions, are also carried out in parallel. Parallel computations are performed using Parallel Virtual Machine (PVM) library. First, a si

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24

Abdo, Mohammed. "Theoretical and computational analysis of airfoils in steady and unsteady flows." Thesis, McGill University, 2004. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=84871.

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This dissertation studies three aspects of airfoil flows: (i) second-order theoretical solutions of airfoils in steady flows; (ii) unsteady solutions for oscillating flexible airfoils; and (iii) numerical analysis of airfoil flows at low Reynolds numbers.<br>The first part presents simple and efficient analytical solutions in closed form for the velocity and pressure distributions on airfoils of arbitrary shapes in steady flows, which are obtained using special singularities in the expression of the fluid velocity. A second-order accurate method is first developed for airfoils in invisc

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25

Abdo, Mohammed. "Analysis of steady and unsteady flows past fixed and oscillating airfoils." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape4/PQDD_0032/MQ64209.pdf.

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26

Walker, William Paul. "Optimization of Harmonically Deforming Thin Airfoils and Membrane Wings for Optimum Thrust and Efficiency." Diss., Virginia Tech, 2012. http://hdl.handle.net/10919/27748.

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This dissertation presents both analytical and numerical approaches to optimizing thrust and thrust efficiency of harmonically deforming thin airfoils and membrane wings. A frequency domain unsteady aerodynamic theory for deformable thin airfoils, with Chebychev polynomials as the basis functions is presented. Stroke-averaged thrust and thrust efficiency expressions are presented in a quadratic matrix form. The motion and deformation of the airfoil is optimized for maximum thrust and efficiency. Pareto fronts are generated showing optimum deformation conditions (magnitude and phase) for va

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27

Benson, Hewett A. O. "Apparent-mass and on-board circulation of Joukowski airfoils and cascades in severe unsteady motion." Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/14523.

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28

Gunaydinoglu, Erkan. "Low Reynolds Number Aerodynamics Of Flapping Airfoils In Hover And Forward Flight." Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/12612397/index.pdf.

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The scope of the thesis is to numerically investigate the aerodynamics of flapping airfoils in hover and forward flight. The flowfields around flapping airfoils are computed by solving the governing equations on moving and/or deforming grids. The effects of Reynolds number, reduced frequency and airfoil geometry on unsteady aerodynamics of flapping airfoils undergoing pure plunge and combined pitch-plunge motions in forward flight are investigated. It is observed that dynamic stall of the airfoil is the main mechanism of lift augmentation for both motions at all Reynolds numbers ranging from 1

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29

Kissing, Johannes Maximillian Emanuel [Verfasser], Cameron [Akademischer Betreuer] Tropea, and Laurant [Akademischer Betreuer] David. "Investigation and Control of Unsteady Flow Conditions on Airfoils / Johannes Maximillian Emanuel Kissing ; Cameron Tropea, Laurant David." Darmstadt : Universitäts- und Landesbibliothek, 2020. http://d-nb.info/1223095401/34.

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30

Kissing, Johannes Maximillian Emanuel Verfasser], Cameron [Akademischer Betreuer] [Tropea, and Laurant [Akademischer Betreuer] David. "Investigation and Control of Unsteady Flow Conditions on Airfoils / Johannes Maximillian Emanuel Kissing ; Cameron Tropea, Laurant David." Darmstadt : Universitäts- und Landesbibliothek, 2020. http://nbn-resolving.de/urn:nbn:de:tuda-tuprints-142017.

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31

Baskan, Ozge. "Experimental And Numerical Investigation Of Flow Field Around Flapping Airfoils Making Figure-of-eight In Hover." Master's thesis, METU, 2009. http://etd.lib.metu.edu.tr/upload/2/12611155/index.pdf.

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ABSTRACT EXPERIMENTAL AND NUMERICAL INVESTIGATION OF FLOW FIELD AROUND FLAPPI G AIRFOILS MAKING FIGURE-OF-EIGHT IN HOVER BASKAN, &Ouml<br>zge M.Sc., Department of Aerospace Engineering Supervisor: Prof. Dr. H. Nafiz Alemdaroglu September 2009, 94 pages The aim of this study is to investigate the flow field around a flapping airfoil making figure-of-eight motion in hover and to compare these results with those of linear flapping motion. Aerodynamic characteristics of these two-dimensional flapping motions are analyzed in incompressible, laminar flow at very low Reynolds numbers regime using bot

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32

Widmann, Alexander Guido Martin [Verfasser], Cameron [Akademischer Betreuer] Tropea, and Laurent [Akademischer Betreuer] David. "Formation and Detachment of Leading Edge Vortices on Unsteady Airfoils / Alexander Guido Martin Widmann. Betreuer: Cameron Tropea ; Laurent David." Darmstadt : Universitäts- und Landesbibliothek Darmstadt, 2015. http://d-nb.info/1111910723/34.

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33

Gonzalez, Salcedo Alvaro. "Development of a potential panel code for unsteady modelling of 2D airfoils in practical applications of large wind turbines." Thesis, Imperial College London, 2018. http://hdl.handle.net/10044/1/61470.

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The present work is an effort to improve airfoil modelling in wind energy applications, specifically for large wind turbine blades. A new model based on inviscid panel methods with a free vortex wake is proposed for the aerodynamic representation of deforming and moving airfoils in a wide range of operating conditions. Large rotors (above 5MW) operate in a challenging environment in terms of complex inflow conditions and dynamics of the wind turbine. The consequence for the blade sections is a significant variation of the local inflow, leading to unsteady conditions which can largely affect th

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34

Krinshnamurthy, R. "Kinetic Flux Vector Splitting Method On Moving Grids (KFMG) For Unsteady Aerodynamics And Aeroelasticity." Thesis, Indian Institute of Science, 2001. http://hdl.handle.net/2005/288.

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Analysis of unsteady flows is a very challenging topic of research. A decade ago, potential flow equations were used to predict unsteady pressures on oscillating bodies. Recognising the fact that nonlinear aerodynamics is essential to analyse unsteady flows accurately, particularly in transonic and supersonic flows, different Euler formulations operating on moving grids have emerged recently as important CFD tools for unsteady aerodynamics. Numerical solution of Euler equations on moving grids based on upwind schemes such as the ones due to van Leer and Roe have been developed for the purpose

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35

Cantoni, Lorenzo. "Load Control Aerodynamics in Offshore Wind Turbines." Thesis, KTH, Kraft- och värmeteknologi, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-291417.

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Due to the increase of rotor size in horizontal axis wind turbine (HAWT) during the past 25 years in order to achieve higher power output, all wind turbine components and blades in particular, have to withstand higher structural loads. This upscalingproblem could be solved by applying technologies capable of reducing aerodynamic loads the rotor has to withstand, either with passive or active control solutions. These control devices and techniques can reduce the fatigue load upon the blades up to 40% and therefore less maintenance is needed, resulting in an important money savings for the wind

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36

Chen, Da-Zhi, and 陳大志. "Unsteady motion airfoil experiment." Thesis, 1997. http://ndltd.ncl.edu.tw/handle/03615475481054261482.

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37

Huang, Chih-Yuan, and 黃智源. "Unsteady structures of a low Reynolds number airfoil." Thesis, 1997. http://ndltd.ncl.edu.tw/handle/38069237198680982116.

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碩士<br>國立台灣工業技術學院<br>機械工程技術研究所<br>85<br>Characteristics of unsteady flow on the suction surface and in the wake re-gion of a NACA0012 cantilever wing operated in low-Reynolds number are studied.Surface oil-flow technique is employed to visualize the flow patterns on the suction surface. Hot-wire anemometers are used to characterize the frequency domain of the unsteady flow structure in the wake region. Five characteristicsurface flow modes are classified in the domain of chord Reynolds numbe

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38

Stockdill, Barton Thomas. "Turbulence modelling of unsteady separated flow over an airfoil." 2003. http://hdl.handle.net/1828/384.

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39

Gharali, Kobra. "Pitching airfoil study and freestream effects for wind turbine applications." Thesis, 2013. http://hdl.handle.net/10012/7833.

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A Horizontal Axis Wind Turbine (HAWT) experiences imbalanced loads when it operates under yaw loads. For each blade element of the aerodynamically imbalanced rotor, not only is the angle of attack unsteady, but also the corresponding incident velocity, a fact usually unfairly ignored. For the unsteady angle of attack, a pitch oscillating airfoil has been studied experimentally and numerically when 3.5×10⁴<Re<10⁵. For small wind tunnel airfoils, Particle Image Velocimetry (PIV) was utilized to determine the aerodynamic loads and the pressure field where other measurement techniques are ei

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40

Rumpfkeil, Markus Peer. "Airfoil Optimization for Unsteady Flows with Application to High-lift Noise Reduction." Thesis, 2008. http://hdl.handle.net/1807/17241.

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The use of steady-state aerodynamic optimization methods in the computational fluid dynamic (CFD) community is fairly well established. In particular, the use of adjoint methods has proven to be very beneficial because their cost is independent of the number of design variables. The application of numerical optimization to airframe-generated noise, however, has not received as much attention, but with the significant quieting of modern engines, airframe noise now competes with engine noise. Optimal control techniques for unsteady flows are needed in order to be able to reduce airframe-genera

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41

Choi, Jeesoon. "Unsteady Aerodynamics and Optimal Control of an Airfoil at Low Reynolds Number." Thesis, 2016. https://thesis.library.caltech.edu/9808/1/Jeesoon%20Choi%20Caltech%20Thesis%20%28Jun%2010%202016%29.pdf.

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As opposed to conventional air vehicles that have fixed wings, small birds and insects are known to flap their wings at higher angles of attack. The vortex produced at the tip of the wing, known as the leading-edge vortex (LEV), plays an important role to enhance lift during its flight. In this thesis, we analyze the influence of these vortices on aerodynamic forces that could be beneficial to micro-air vehicle performance and efficiency. The flow structures associated with simple harmonic motions of an airfoil are first investigated. The characteristics of the time-averaged and fluctuating fo

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42

Pruski, Brandon. "Leading Edge Flow Structure of a Dynamically Pitching NACA 0012 Airfoil." Thesis, 2012. http://hdl.handle.net/1969.1/148372.

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The leading edge flow structure of the NACA 0012 airfoil is experimentally investigated under dynamic stall conditions (M = 0.1; α = 16.7◦, 22.4◦; Rec = 1× 10^6) using planar particle image velocimetry. The airfoil was dynamically pitched about the 1/4 chord at a reduced frequency, k = 0.1. As expected, on the upstroke the flow remains attached in the leading edge region above the static stall angle, whereas during downstroke, the flow remains separated below the static stall angle. A phase averaging procedure involving triple velocity decomposition in combination with the Hilbert transform en

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43

McClung, Aaron M. "Development and validation of an unsteady panel code to model airfoil aeromechanical response." 2004. http://digital.library.okstate.edu/etd/umi-okstate-1045.pdf.

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44

WANG, ZI-YI, and 王子逸. "Control of separated flow over a 2-D airfoil by an unsteady flap." Thesis, 1992. http://ndltd.ncl.edu.tw/handle/60488448202548671945.

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45

Li, Jun Hui, and 李俊輝. "Unsteady pressure measurements on a pitching airfoil and estimation of lift from wake surveys." Thesis, 1995. http://ndltd.ncl.edu.tw/handle/83624666831421561481.

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46

Gornowicz, Galen Gerald. "Continuous-field Image-Correlation Velocimetry and its application to unsteady flow over an airfoil." Thesis, 1997. https://thesis.library.caltech.edu/3021/1/Gornowicz_gg_1997.pdf.

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Continuous-field Image Correlation Velocimetry (ICV) is an extension to the ICV technique of Tokumaru & Dimotakis (1995). The method determines the optical flow in sequences of images, and relies on a convected Lagrangian marker, e.g., a conserved scalar field, or particles, etc. The method has been applied to several simulated-flow test cases and results are presented for the error of the method, with and without noise added to the correlated test-images. The results of further tests are reported, for two laboratory flows; a NACA-0012 airfoil at high angle of attack, and a transverse jet

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47

Arjun, B. S. "Motion Optimistion Of Plunging Airfoil Using Swarm Algorithm." Thesis, 2008. http://hdl.handle.net/2005/708.

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Micro Aerial Vehicles (MAVs) are battery operated, remote controlled miniature flying vehicles. MAVs are required in military missions, traffic management, hostage situation surveillance, sensing, spying, scientific, rescue, police and mapping applications. The essential characteristics required for MAVs are: light weight, maneuverability, ease of launch in variety of conditions, ability to operate in very hostile environments, stealth capabilities and small size. There are three main classes of MAVs : fixed, rotary and flapping wing MAV’s. There are some MAVs which are combinations of th

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48

Sen, Nilanjan Rahn Christopher D. "Inviscid unsteady aerodynamic models of airfoils moving near boundaries." 2008. http://etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-3147/index.html.

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49

Kissing, Johannes Maximillian Emanuel. "Investigation and Control of Unsteady Flow Conditions on Airfoils." Phd thesis, 2020. https://tuprints.ulb.tu-darmstadt.de/14201/1/Dissertation_Kissing.pdf.

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In this thesis, efficiency enhancement approaches for two unsteady aerodynamic scenarios are considered to provide the basis for future improvements. The first scenario addresses transient inflow conditions on a stationary airfoil, representative of gust loads on wind turbine blades or bridge decks. It aims at the experimental validation of aerodynamic transfer functions, known as the Sears and Atassi formulations, which allow for a prediction of unsteady loads. Both functions are found to be capable of load prediction if inflow assumptions are carefully reproduced. It is also shown that n

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50

Widmann, Alexander Guido Martin. "Formation and Detachment of Leading Edge Vortices on Unsteady Airfoils." Phd thesis, 2015. https://tuprints.ulb.tu-darmstadt.de/4670/7/Thesis_korrigiert_final_3.pdf.

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The unsteady velocity field around a pitching and plunging airfoil has been investigated whereby two different mechanisms leading to the detachment of leading edge vortices, which form at the suction side of the airfoil during a motion cycle, were of central interest. One of these mechanisms is analogous to the classical vortex shedding mechanisms behind bluff bodies. The second mechanism is independent of any geometrical length and occurs as a result of the viscous/inviscid interaction between the leading edge vortex and the boundary layer on the airfoil. The mass transferred from the shear

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