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Relevant bibliographies by topics / Active aerodynamics / Dissertations / Theses

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Dissertations / Theses on the topic 'Active aerodynamics'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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1

Pesiridis, Apostolos. "Turbocharger turbine unsteady aerodynamics with active control." Thesis, Imperial College London, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.498148.

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2

Brzozowski, Daniel Paul. "Dynamic control of aerodynamic forces on a moving platform using active flow control." Diss., Georgia Institute of Technology, 2011. http://hdl.handle.net/1853/42930.

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The unsteady interaction between trailing edge aerodynamic flow control and airfoil motion in pitch and plunge is investigated in wind tunnel experiments using a two degree-of-freedom traverse which enables application of time-dependent external torque and forces by servo motors. The global aerodynamic forces and moments are regulated by controlling vorticity generation and accumulation near the trailing edge of the airfoil using hybrid synthetic jet actuators. The dynamic coupling between the actuation and the time-dependent flow field is characterized using simultaneous force and particle im

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3

Wu, Dong-Nan. "Active bounded-state vibration control for structural applications." Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/12326.

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4

Chowdhury, Subhradeep. "An experimental investigation of active stall control in compression systems." Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/12341.

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5

Griffin, Steven F. "Acoustic replication in smart structure using active structural/acoustic control." Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/13085.

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6

Alan, Luton J. "Numerical simulations of subsonic aeroelastic behavior and flutter suppression by active control /." This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-03172010-020348/.

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7

Williams, Nathan M. "Active flow control on a nonslender delta wing." Thesis, University of Bath, 2009. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.501373.

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The effects of active flow control by oscillatory blowing at the leading edge of a nonslender delta wing with a Λ=50° sweep angle have been investigated. Pressure measurements and Particle Image Velocimetry measurements were conducted on a half wing to investigate the formation of leading edge vortices for oscillatory blowing, compared to the stalled flow for the no blowing case. Stall has been delayed by up to 8, and significant increases in the upper surface suction force have been observed. Velocity measurements show that shear layer reattachment is promoted with forcing, and a vortex flow

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8

Stiborová, Dana. "Aktivní aerodynamické prvky osobních vozidel." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-318777.

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In this diploma thesis active aerodynamic components are designed, specifically brake cooling duct and active automotive wing. Cooling duct prototype and also active regulation controlling electronics including the software were created. Road test was performed to measure the duct parameters. Construction design and the active regulation function of the automotive wing were created. The influence of the wing on aerodynamic characteristics of the car was determined.

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9

Krichene, Assaad. "Active identification and control of aerodynamic instabilities in axial and centrifugal compressors." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12062.

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10

Kuchan, Abigail. "The integration of active flow control devices into composite wing flaps." Thesis, Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/44758.

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Delaying stall is always an attractive option in the aerospace industry. The major benefit of delaying stall is increased lift during takeoff and landings as well as during high angle of attack situations. Devices, such as fluidic oscillators, can be integrated into wing flaps to help delay the occurrence of stall by adding energized air to the airflow on the upper surface of the wing flap. The energized air from the oscillator allows the airflow to remain attached to the upper surface of the wing flap. The fluidic oscillator being integrated in this thesis is an active flow control device (A

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11

Erlhoff, Ethan Bruce. "Distributed Forcing on a 3D Bluff Body with a Blunt Base, An Experimental Active Drag Control Approach." DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/879.

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This paper seeks to explore the effects of an active drag control method known as distributed forcing on a 3D bluff body with a blunt base. The 9.5 x 15.25 x 3 inch aluminum model constructed for this experiment has an elliptically shaped nose and rectangular aft section. The model is fitted with four, 12 Volt fans, forcing the freestream air into and out of 1 mm thick slots on the upper and lower trailing edges. The forcing is steady in time, held at a constant forcing velocity though all Reynolds numbers, but varies roughly sinusoidally in the spanwise direction across the model. Testing

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12

Luton, J. Alan. "Numerical simulations of subsonic aeroelastic behavior and flutter suppression by active control." Thesis, Virginia Tech, 1991. http://hdl.handle.net/10919/41681.

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<p>A method for predicting the unsteady, subsonic, aeroservoelastic response of a wing has been developed. The air, wing, and control surface are considered to be a single dynamical system. All equations are solved simultaneously in the time domain by a predictor-corrector method. The scheme allows nonlinear aerodynamic and structural models to be used and subcritical, critical, and supercritical aeroelastic behavior may be modeled without restrictions to small disturbances or periodic motions. A vortex-lattice method is used to model the aerodynamics. This method accounts for nonlinear effect

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13

Eveker, Kevin M. "Model Development for active control of stall phenomena in aircraft gas turbine engines." Diss., Georgia Institute of Technology, 1993. http://hdl.handle.net/1853/12363.

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14

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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15

Harrison, Neal A. "Active Flow Control of a Boundary Layer Ingesting Serpentine Diffuser." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/34163.

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The use of serpentine boundary layer ingesting (BLI) diffusers offers a significant benefit to the performance of Blended Wing Body aircraft. However, the inherent diffuser geometry combined with a thick ingested boundary layer creates strong secondary flows that lead to severe flow distortion at the engine face, increasing the possibility of engine surge. This study investigated the use of enabling active flow control methods to reduce engine-face distortion. An ejector-pump based system of fluidic actuators was used to directly manage the diffuser secondary flows. This system was modeled co

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16

Poole, Sean. "The development of a segmented variable pitch small horizontal axis wind turbine with active pitch control." Thesis, Nelson Mandela Metropolitan University, 2013. http://hdl.handle.net/10948/d1020583.

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Small scale wind turbines operating in an urban environment produce dismal amounts of power when compared to their expected output [1-4]. This is largely due to the gusty wind conditions found in an urban environment, coupled with the fact that the wind turbines are not designed for these conditions. A new concept of a Segmented Variable Pitch (SVP) wind turbine has been proposed, which has a strong possibility to perform well in gusty and variable wind conditions. This dissertation explains the concept of a SVP wind turbine in more detail and shows analytical and experimental results relating

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17

Andrews, Stuart P. "Modelling and simulation of flexible aircraft : handling qualities with active load control." Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/7705.

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The study of the motion of manoeuvring aircraft has traditionally considered the aircraft to be rigid. This simplifying assumption has been shown to give quite accurate results for the flight dynamics of many aircraft types. As modern transport aircraft have developed however, there has been a marked increase in the size and weight of these aircraft. This trend is likely to continue with the development of future blended-wing-body and supersonic transport aircraft. This increase in size and weight has brought about a unique set of aeroelastic and handling quality issues. The aerodynamic forces

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18

Yugulis, Kevin Lee. "High Subsonic Cavity Flow Control Using Plasma Actuators." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1345552086.

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19

Sudak, Peter J. "Experimental Investigation of Active Wingtip Vortex Control using Synthetic Jet Actuators." DigitalCommons@CalPoly, 2014. https://digitalcommons.calpoly.edu/theses/1305.

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An experiment was performed in the Cal Poly Mechanical Engineering 2x2 ft wind tunnel to quantify the effect of spanwise synthetic jet actuation (SJA) on the drag of a NACA 0015 semispan wing. The wing, which was designed and manufactured for this experiment, has an aspect ratio of 4.20, a span of 0.427 m (16.813”), and is built around an internal array of piezoelectric actuators, which work in series to create a synthetic jet that emanates from the wingtip in the spanwise direction. Direct lift and drag measurements were taken at a Reynolds Number of 100,000 and 200,000 using a load cell/slid

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20

Hussain, Ali. "The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance." The Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1555516043121521.

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21

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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22

Walker, Michael Monroe. "Replicating the Effects of a Passive Boundary-Layer Fence via Active Flow Control." The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1524146958877311.

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23

Patel, Umesh. "Control authority and the design of active controllers for buffet suppression of the F-15 and F/A-18." Thesis, Georgia Institute of Technology, 2003. http://hdl.handle.net/1853/12161.

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24

Guskey, Christopher R. "NEAR WALL SHEAR STRESS MODIFICATION USING AN ACTIVE PIEZOELECTRIC NANOWIRE SURFACE." UKnowledge, 2013. http://uknowledge.uky.edu/me_etds/27.

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An experimental study was conducted to explore the possible application of dynamically actuated nanowires to effectively disturb the wall layer in fully developed, turbulent channel flow. Actuated nanowires have the potential to be used for the mixing and filtering of chemicals, enhancing convective heat transfer and reducing drag. The first experimental evidence is presented suggesting it is possible to manipulate and subsequently control turbulent flow structures with active nanowires. An array of rigid, ultra-long (40 μm) TiO2 nanowires was fabricated and installed in the bounding wall of t

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25

Vasilescu, Roxana. "Helicopter blade tip vortex modifications in hover using piezoelectrically modulated blowing." Diss., Available online, Georgia Institute of Technology, 2004:, 2004. http://etd.gatech.edu/theses/available/etd-11192004-165246/unrestricted/vasilescu%5Froxana%5F200412%5Fphd.pdf.

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Thesis (Ph. D.)--Aerospace Engineering, Georgia Institute of Technology, 2005.<br>Dancila, Stefan, Committee Chair ; Sankar, Lakshmi, Committee Member ; Ruzzene, Massimo, Committee Member ; Smith, Marilyn, Committee Member ; Yu, Yung, Committee Member. Vita. Includes bibliographical references.

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26

Woszidlo, Rene, and Rene Woszidlo. "PARAMETERS GOVERNING SEPARATION CONTROL WITH SWEEPING JET ACTUATORS." Diss., The University of Arizona, 2011. http://hdl.handle.net/10150/203475.

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Parameters governing separation control with sweeping jet actuators over a deflected flap are investigated experimentally on a generic "Multiple Flap Airfoil" (MFA). The model enables an extensive variation of geometric and aerodynamic parameters to aid the scaling of this novel flow control method to full-size applications.Sweeping jets exit from discrete, millimeter-scale nozzles distributed along the span and oscillate from side-to-side. The sweeping frequency is almost linearly dependent on the supplied flowrate per actuator. The measured thrust exerted by a row of actuators agrees well wi

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27

Mariette, Kevin. "Contrôle en boucle fermée pour la réduction active de traînée aérodynamique des véhicules." Thesis, Lyon, 2020. http://www.theses.fr/2020LYSEI088.

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Le contrôle actif de l’écoulement à l’arrière des véhicules se déplaçant à grande vitesse est un moyen de diminuer efficacement la consommation énergétique des véhicules par la réduction de la traînée aérodynamique. L’intérêt des méthodes actives est leur possible adéquation avec des conditions environnementales variables pour une modification minimale de la forme des véhicules, contrairement aux systèmes exclusivement passifs (profilage, ailerons aérodynamiques …). Toutefois, le contrôle actif nécessite un apport d’énergie qui réduit sa rentabilité énergétique finale. À l’aide d’essais expéri

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28

McHugh, Garrett R. "An Experimental Investigation in the Mitigation of Flutter Oscillation Using Shape Memory Alloys." University of Akron / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=akron1479119992818089.

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29

Lopera, Javier. "Aerodynamic Control of Slender Bodies from Low to High Angles of Attack through Flow Manipulation." Connect to Online Resource-OhioLINK, 2007. http://www.ohiolink.edu/etd/view.cgi?acc_num=toledo1177504352.

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30

Littlewood, Rob. "Novel methods of drag reduction for squareback road vehicles." Thesis, Loughborough University, 2013. https://dspace.lboro.ac.uk/2134/12534.

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Road vehicles are still largely a consumer product and as such the styling of a vehicle becomes a significant factor in how commercially successful a vehicle will become. The influence of styling combined with the numerous other factors to consider in a vehicle development programme means that the optimum aerodynamic package is not possible in real world applications. Aerodynamicists are continually looking for more discrete and innovative ways to reduce the drag of a vehicle. The current thesis adds to this work by investigating the influence of active flow control devices on the aerodynamic

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31

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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32

Baleriola, Sophie. "Etude expérimentale de la modification des charges aérodynamiques sur pale d'éolienne par du contrôle d'écoulement actif." Thesis, Orléans, 2018. http://www.theses.fr/2018ORLE2029/document.

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L’énergie éolienne est une source d’énergie propre et renouvelable qui fait partie des moyens pour réduire les émissions de gaz à effet de serre et contrer le réchauffement climatique dans le domaine de la production électrique.L’objectif de la thèse est d’optimiser la production d’énergie éolienne par la réduction des fluctuations de charge induites par la turbulence de la couche limite atmosphérique. Ces fluctuations augmentent la fatigue des pales et réduisent la durée de vie des rotors.Cette réduction des fluctuations de charge est réalisée par le biais d’une approche expérimentale et à l’

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33

Sarwar, Wasim. "Active flow control methods for aerodynamic applications." Doctoral thesis, Universitat Politècnica de Catalunya, 2020. http://hdl.handle.net/10803/669325.

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The cylinder in cross flow has been the subject of many numerical and experimental studies since it provides a deep insight of the physical phenomena occurring in a wide range of flow regimes. Despite a number of investigations at Reynolds number (Re = 3900), there has been a constant debate on the important aspects of the flow such as spanwise resolutions, lateral domain extent, convergence of turbulent statistics in the near wake, the so called U-V streamwise velocity profiles at x = 1D, where D is the cylinder diameter, and the critical Re for the onset of shear layer instability together

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34

Barden, Jason. "Active Aerodynamic Control of Heavy Goods Vehicles." Thesis, Cranfield University, 2013. http://dspace.lib.cranfield.ac.uk/handle/1826/9293.

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Most heavy goods vehicles in service today are fitted with add-on aerodynamic devices. The most common of which is the cab-mounted roof deflector. Such devices provide appreciable drag savings, however, they are often not optimised for the trailer. When a wind yaw angle is present, their savings also diminish as the yaw angle increases. The work conducted within this thesis investigated the possibility of using an adjustable deflector for active flow control. The optimum deflector height for a given trailer height was initially investigated using wind tunnel testing. The variation of this opti

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35

Yeshala, Nandita. "A coupled lattice Boltzmann-Navier-Stokes methodology for drag reduction." Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/37097.

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Helicopter performance is greatly influenced by its drag. Pylons, fuselage, landing gear, and especially the rotor hub of a helicopter experience large separated flow regions, even under steady level flight conditions the vehicle has been designed for, contributing to the helicopter drag. Several passive and active flow control concepts have been studied for reducing helicopter drag. While passive flow control methods reduce drag, they do so at one optimized design condition. Therefore, passive drag reduction methods may not work for helicopters that operate under widely varying flight conditi

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36

Metka, Matthew. "Application of Fluidic Oscillator Separation Control to a Square-back Vehicle Model." The Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1439205355.

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37

Kepets, Mark Alexander 1978. "Actively conformable aerodynamic surfaces." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/82226.

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38

Čermák, Jakub. "Numerická analýza bio-mimetického konceptu řízení proudu na povrchu křídla." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-317186.

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V této diplomové práci je provedena optimalizace profilu křídla vybaveného elastickou klapkou umístěnou na horní straně profilu. Optimalizační proces je proveden s vyžitím CFD prostředků, konkrétně URANS metody. V prvních kapitolách je popsána historie vývoje křídla vybaveného pohyblivými klapkami. Práce pokračuje popisem a zdůvodněním volby numerické metody. Vytvoření geometrie a výpočetní sítě je krátce popsáno. V práci je také prezentována validace a verifikace dané výpočetní metody. Případová studie je zaměřena na profil LS(1)-0417mod vybavený 20%, 30% a 40% dlouhou, pevnou kalpkou na různ

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39

Guttag, Mark A. (Mark Andrew). "Aerodynamic drag on deformable and active structures in high Reynolds number conditions." Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/115720.

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Thesis: Ph. D., Massachusetts Institute of Technology, Department of Mechanical Engineering, 2018.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 141-150).<br>We explore the effect of topography on the aerodynamic behavior of deformable structures, at high Reynolds numbers. We first introduce a novel mechanism to control the aerodynamic drag on cylinders, in the critical Reynolds number regime. We created both axially grooved and dimpled specimens, comprised of latex membranes stretched over rigid acrylic skeletons. By decreasing the internal pressure of

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40

Zink, Paul Scott. "A methodology for robust structural design with application to active aeroelastic wings." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12424.

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41

Chadwick, Kenneth Michael. "An actively cooled floating element skin friction balance for direct measurement in high enthalpy supersonic flows." Diss., This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-07282008-134703/.

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42

Lassaux, Guillaume 1977. "High-fidelity reduced-order aerodynamic models : application to active control of engine inlets." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/82238.

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43

Silkowski, Peter D. (Peter Daniel). "Aerodynamic design of moveable inlet guide vanes for active control of rotating stall." Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/42181.

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44

Pettit, Gregory William. "Model to Evaluate the Aerodynamic Energy Requirements of Active Materials in Morphing Wings." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/36364.

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A computational model is presented which predicts the force, stroke, and energy needed to overcome aerodynamic loads encountered by morphing wings during aircraft maneuvers. This low-cost model generates wing section shapes needed to follow a desired flight path, computes the resulting aerodynamic forces using a unique combination of conformal mapping and the vortex panel method, computes the longitudinal motion of the simulated aircraft, and closes the loop with a zero-error control law. The aerodynamic force prediction method has been verified against two more expensive codes. This overal

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45

Karaolis, Nicos M. "The design of fibre reinforced composite blades for passive and active wind turbine rotor aerodynamic control." Thesis, University of Reading, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.235661.

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46

Djayapertapa, Lesmana. "A computational method for coupled aerodynamic-structural calculations in unsteady transonic flow with active control study." Thesis, University of Bristol, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.341506.

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47

Shukla, Poorva Jahnukumar. "Active Flight Path Control for an Induced Spin Flight Termination System." Thesis, Virginia Tech, 2017. http://hdl.handle.net/10919/78881.

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In this thesis, we describe a method for controlling the cycle-averaged velocity direction of a fixed-wing aircraft in an unpowered, helical descent. While the aircraft propulsion system is disabled, either intentionally or due to a failure, the aerodynamic control surfaces (aileron, elevator, and rudder) are assumed to be functional. Our approach involves two steps: (i) establishing a stable, steady, helical motion for which the control surfaces are not fully deflected and (ii) modulating the aircraft control surfaces about their nominal positions to ``slant'' the helical flight path in a des

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48

Karadal, Fatih Mutlu. "Active Flutter Suppression Of A Smart Fin." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/12609830/index.pdf.

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This study presents the theoretical analysis of an active flutter suppression methodology applied to a smart fin. The smart fin consists of a cantilever aluminum plate-like structure with surface bonded piezoelectric (PZT, Lead- Zirconate-Titanate) patches. A thermal analogy method for the purpose of modeling of piezoelectric actuators in MSC&reg<br>/NASTRAN based on the analogy between thermal strains and piezoelectric strains was presented. The results obtained by the thermal analogy were compared with the reference results and very good agreement was observed. The unsteady aerodynamic loa

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49

Jeřábek, Lukáš. "Aerodynamický návrh posledního stupně parní turbíny." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2018. http://www.nusl.cz/ntk/nusl-378638.

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Diploma thesis deals with calculations of a steam turbine with two uncontrolled extraction points according to the assignment, aerodynamics of the last two stages and operating range with respect to ventilation, range of performance and straining of the last blading under the large condensation pressure deviations. For the first three stages the calculation of prismatic action blades is executed. The fourth and the fifth stages are designed with inconstant reaction over the blades length and their calculation is executed with constant circulation method. For these stages, aerofoil design with

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50

Lahaye, Arnaud. "Caractérisation de l'écoulement autour d'un corps de Ahmed à culot droit." Thesis, Orléans, 2014. http://www.theses.fr/2014ORLE2019.

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Le contrôle actif d’écoulement est actuellement étudié dans le but d’améliorer les performances aérodynamiques des véhicules aériens ou terrestres. La diminution de la traînée permettrait de réduire la consommation de carburants fossiles et donc l’émission des gaz à effet de serre des véhicules. Les actionneurs fluidiques sont utilisés comme dispositifs de contrôle depuis une quinzaine d’année. Le contrôle par jet synthétique semble être le plus adapté à une application sur un véhicule de série dans la mesure où l’actionneur ne doit pas être alimenté en fluide. Le travail présenté dans cette t

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