Relevant bibliographies by topics / Control flow separation / Dissertations / Theses
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Dissertations / Theses on the topic 'Control flow separation'

Author: Grafiati
Published: 28 May 2022
Last updated: 31 July 2025

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1

Schulmeister, James Crandall. "Flow separation control with rotating cylinders." Thesis, Massachusetts Institute of Technology, 2012. http://hdl.handle.net/1721.1/78196.

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Thesis (S.M. in Ocean Engineering)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2012.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (p. 61-62).<br>The hydrodynamic forces on ocean vehicles increase dramatically during sharp maneuvers as compared to forward motion due to large areas of separated flow. These large forces severely limit maneuverability and reduce efficiency. Applying active flow separation control to ocean vehicles would reduce resistance during maneuvers and thereby improve maneuvering performance. In this thesis I di
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2

Nilsson, Stefan. "Flow Separation Control Utilizing Plasma Actuators." Thesis, Luleå tekniska universitet, Rymdteknik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-69107.

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The goal of this thesis was to both theoretically and experimentally show the effect of a plasma actuator for flow separation control.  In the theoretical part a solver was implemented in MATLAB code, to solve the governing equations describing the plasma actuator.  The experimental part included PIV (Particle Image Velocimetry) measurements of the velocity field induced by the plasma actuator, visualization of the effect in a wind tunnel and the development of a simple model of the plasma actuator based on the empirical result whose purpose is to be used in CFD (Computational Fluid Dynamics).
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3

KASLIWAL, AMIT. "FLOW SEPARATION CONTROL FOR CYLINDER FLOW AND CASCADE FLOW USING GENERATOR JETS." University of Cincinnati / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1141413192.

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4

Kim, Kihwan. "Feedback control of flow separation using synthetic jets." Texas A&M University, 2005. http://hdl.handle.net/1969.1/3252.

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The primary goal of this research is to assess the effect of synthetic jets on flow separation and provide a feedback control strategy for flow separation using synthetic jets. The feedback control synthesis is conducted based upon CFD simulation for a rounded backward-facing step. The results of the synthetic jet experiments on an airfoil showed that synthetic jets have the potential for controlling the degree of flow separation beyond delaying the onset of flow separation. In the simulation, while the jet is ejected slightly upstream from the separation point, the feedback pressure signal is
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5

Sunneechurra, Kailash. "Leading-edge flow separation control for high-lift." Thesis, University of Manchester, 2010. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.517838.

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6

Kasliwal, Amit. "Flow separation control for cylinder flow and cascade flow using vortex generator jets." Cincinnati, Ohio : University of Cincinnati, 2006. http://www.ohiolink.edu/etd/view.cgi?acc%5Fnum=ucin1141413192.

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Thesis (M.S.)--University of Cincinnati, 2006.<br>Title from electronic thesis title page (viewed Apr. 18, 2006). Includes abstract. Keywords: Flow Separation; Low Pressure Turbine Cascade; LPT Cascade; Flow over Cylinder; Vortex Generator Jets; VGJ; Multiblock Grid. Includes bibliographical references.
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7

Lögdberg, Ola. "Turbulent Boundary Layer Separation and Control." Doctoral thesis, KTH, Linné Flow Center, FLOW, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-9821.

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Boundary layer separation is an unwanted phenomenon in most technical applications, as for instance on airplane wings, ground vehicles and in internal flow systems. If separation occurs, it causes loss of lift, higher drag and energy losses. It is thus essential to develop methods to eliminate or delay separation.In the present experimental work streamwise vortices are introduced in turbulent boundary layers to transport higher momentum fluid towards the wall. This enables the boundary layer to stay attached at  larger pressure gradients. First the adverse pressure gradient (APG) separation bu
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8

Urzynicok, Frank. "Separation control by flow-induced oscillations of a resonator." [S.l.] : [s.n.], 2003. http://deposit.ddb.de/cgi-bin/dokserv?idn=968424929.

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9

Pasquale, Laura. "Robust feedback control of flow separation using plasma actuators." Thesis, University of Nottingham, 2017. http://eprints.nottingham.ac.uk/47943/.

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This thesis addresses the problem of controlling the unsteady flow separation over an aerofoil using plasma actuators, with the aim of improving the performance of fluid systems through the use of robust feedback controllers. Despite the complexity of the dynamics of interest, it is shown how the problem of controlling flow separation can be successfully formulated and solved as a simple output regulation problem. First, a novel control-oriented reduced-order model for nonlinear systems evolving on attractors is obtained. Its application to the incompressible Navier-Stokes equations is propose
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10

Resendiz, Rosas Celerino. "Numerical simulation of flow separation control by oscillatory fluid injection." Diss., Texas A&M University, 2003. http://hdl.handle.net/1969.1/2461.

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In this work, numerical simulations of flow separation control are performed. The sep-aration control technique studied is called 'synthetic jet actuation'. The developed code employs a cell centered finite volume scheme which handles viscous, steady and unsteady compressible turbulent flows. The pulsating zero mass jet flow is simulated by imposing a harmonically varying transpiration boundary condition on the airfoil's surface. Turbulence is modeled with the algebraic model of Baldwin and Lomax. The application of synthetic jet actuators is based in their ability to energize the boundary lay
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11

Tang, Hui. "Performance modelling of synthetic jet actuators for flow separation control." Thesis, University of Manchester, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.595660.

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Active control of flow separation over multi-element high-lift systems of aircraft wings could result in the decrease of drag force, the increase of lift, and the reduction of system complexity. This, in return, lowers fuel consumption and increases profitability, making the goals of both the Kyoto Protocol and the European Vision for 2020 more achievable. To maximise the potential of this technology, forms of actuation with high efficiency, low power consumption, fast response, good reliability, and low cost, are required. The synthetic jet is a kind of jet that on one hand produces zero net
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12

Pern, Nan Jou. "CHARACTERIZATION OF ZERO MASS FLUX FLOW CONTROL FOR LOW SPEED AIRFOIL SEPARATION CONTROL." UKnowledge, 2008. http://uknowledge.uky.edu/gradschool_diss/577.

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An adaptive wing, a zero mass ux ow control device for low speed airfoil separation control, is investigated both experimentally and computationally at low speeds. The adaptive mechanism in the wings provides variable camber that can be actuated across a range of frequencies and amplitudes. Piezoelectric actuators are housed in a NACA 4415 airfoil with a chord length of :203 m. The entire adaptive wing assembly is then wrapped under a layer of latex membrane to provide a exible and smooth upper surface pro le. Experimental diagnostics include ow visualization, particle image velocimetry, as we
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13

Munther, Timothy P. "Characterization of dielectric barrier discharge plasma actuators for flow separation control." Connect to resource, 2007. http://hdl.handle.net/1811/25081.

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Thesis (Honors)--Ohio State University, 2007.<br>Title from first page of PDF file. Document formatted into pages: contains vii, 55 p.; also includes graphics. Includes bibliographical references (p. 55). Available online via Ohio State University's Knowledge Bank.
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14

von, Stillfried Florian. "Computational fluid-dynamics investigations of vortex generators for flow-separation control." Doctoral thesis, KTH, Turbulens, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-94879.

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Many flow cases in fluid dynamics face undesirable flow separation due to ad-verse pressure gradients on wall boundaries. This occurs, for example, due togeometrical reasons as in a highly curved turbine-inlet duct or on flow-controlsurfaces such as wing trailing-edge flaps within a certain angle-of-attack range.Here, flow-control devices are often used in order to enhance the flow and delayor even totally eliminate flow separation. Flow control can e.g. be achieved byusing passive or active vortex generators (VGs) for momentum mixing in theboundary layer of such flows. This thesis focusses on
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15

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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16

Packard, Nathan Owen. "Active Flow Separation Control of a Laminar Airfoil at Low Reynolds Number." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1338315982.

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17

Balasubramanian, Ashwin Kumar. "Modeling of D/C motor driven synthetic jet acutators for flow separation control." Thesis, Texas A&M University, 2003. http://hdl.handle.net/1969.1/1146.

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The objective of this research is to present a theoretical study of the compressibility effects on the performance of an electric D/C motor driven synthetic jet actuator for flow separation control. Hot wire anemometer experiments were conducted to validate the jet exit velocities predicted by the theoretical model. The optimal jet exit velocity required to achieve maximum flow reattachment at reasonable blowing momentum coefficients is predicted. A dynamic electro-acoustic model of the D/C motor driven actuator is developed to accurately predict its performance and efficiency. This model shou
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18

Wang, Shiqi. "Experimental and Numerical Study of Micro-Fluidic Oscillators for Flow Separation Control." Thesis, Toulouse, INSA, 2017. http://www.theses.fr/2017ISAT0017/document.

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Les oscillateurs fluidiques qui peuvent générer des excitations périodiques sont des actionneurs très prometteurs pour des applications de contrôle actif des écoulements. Les oscillations sont en effet complètement auto-induites et produites en l'absence de parties mobiles ce qui rend ces actionneurs très intéressants en termes de fiabilité et de robustesse. Ce travail de thèse avait pour objectif principal d'identifier les mécanismes physiques qui contrôlent la dynamique de fonctionnement de ce type d'oscillateurs fluidiques et de proposer des lignes directrices pour la conception d'oscillate
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19

Ramakumar, Karthik. "ACTIVE FLOW CONTROL OF LOW PRESSURE TURBINE BLADE SEPARATION USING PLASMA ACTUATORS." UKnowledge, 2006. http://uknowledge.uky.edu/gradschool_theses/359.

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The current study examines plasma actuators as flow control devices. The actuators are placed on a turbine blade profile in a 2D turbine cascade for separation flow control. The configuration involves copper strips separated by a layer of dielectric material, across which an AC electric potential in the range of 5 kHz and 5 kV is applied. The efficiency of the actuator is monitored by measuring power input and flow control effectiveness. Preliminary observations are performed for a quiescent case on a flat plate profile to analyze the average and instantaneous velocities generated by the actua
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20

Sahoo, Debashis 1976. "Control of acoustics and store separation in a cavity in supersonic flow." Thesis, Massachusetts Institute of Technology, 2005. http://hdl.handle.net/1721.1/28915.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2005.<br>Includes bibliographical references (p. 137-140).<br>The supersonic flight community is currently faced with two cavity-under-cross-flow related problems, one being the high noise levels inside the cavity and the other being the return of a store into the cavity after being released from inside. This thesis provides a systematic framework to understand the dominant physics in both problems and to provide solutions for ameliorating the problems. For the first problem, an innovative cavity aco
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21

Rethmel, Christopher C. "Airfoil Leading Edge Flow Separation Control Using Nanosecond Pulse DBD Plasma Actuators." The Ohio State University, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=osu1306348260.

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22

Balzer, Wolfgang. "Numerical Investigation of the Role of Free-Stream Turbulence on Boundary-Layer Separation and Separation Control." Diss., The University of Arizona, 2011. http://hdl.handle.net/10150/204289.

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The aerodynamic performance of lifting surfaces operating at low Reynolds number conditions is impaired by laminar separation. Understanding of the physical mechanisms and hydrodynamic instabilities that are associated with laminar separation and the formation of laminar separation bubbles (LSBs) is key for the design and development of effective and efficient active flow control (AFC) devices. For the present work, laminar separation and its control were investigated numerically by employing highly-accurate direct numerical simulations (DNS).For a LSB on a curved plate, the primary and second
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23

Agrawal, Anmol. "Hingeless flow control over an airfoil via distributed actuation." Texas A&M University, 2005. http://hdl.handle.net/1969.1/4919.

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An experimental investigation was undertaken to test the effectiveness of a novel design for controlling the aerodynamics of an airfoil. A synthetic jet actuator (SJA) was placed inside a NACA 0015 airfoil with its jet at 12.5% of the chord length, hereby referred to as the leading edge actuator. Four centrifugal fans across the span were mounted at 70% of the chord and the jet formed by them was located at 99% of the chord, hereby referred to as the trailing edge actuator. The effects of these actuators on the aerodynamic properties were studied, separately and then in conjunction, with varyi
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24

Little, Jesse. "High-Lift Airfoil Separation Control with Dielectric Barrier Discharge Plasma Actuators." The Ohio State University, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=osu1267836038.

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25

Östlund, Jan. "Supersonic flow separation with application to rocket engine nozzles." Doctoral thesis, KTH, Mechanics, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3793.

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<p>The increasing demand for higher performance in rocketlaunchers promotes the development of nozzles with higherperformance, which basically is achieved by increasing theexpansion ratio. However, this may lead to flow separation andensuing instationary, asymmetric forces, so-called side-loads,which may present life-limiting constraints on both the nozzleitself and other engine components. Substantial gains can bemade in the engine performance if this problem can be overcome,and hence different methods of separation control have beensuggested. However, none has so far been implemented in full
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26

Kaya, Muammer. "The effect of air flow rate and froth thickness on batch and continuous flotation kinetics /." Thesis, McGill University, 1985. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=63358.

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27

Stein, Alexander. "Computational analysis of stall and separation control in centrifugal compressors." Diss., Georgia Institute of Technology, 2000. http://hdl.handle.net/1853/11884.

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28

Singhal, Achal Sudhir. "Unsteady Flow Separation Control over a NACA 0015 using NS-DBD Plasma Actuators." The Ohio State University, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=osu148217512319911.

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29

Cheng, Shueh-Hen. "Systematic synthesis of sloppy multicomponent separation sequences." Diss., Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/76510.

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An important process-design problem in multicomponent separations is separation sequencing, which is concerned with the selection of the best method and sequence for a separation system. Essentially all of the published work on this subject has been limited to high-recovery or sharp separations, in which each component to be separated appears in one and only one product stream. In industrial practice, however, it is often useful to permit components that are being separated to appear in two or more product streams. This type of separation results in products that have overlapping components an
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30

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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31

Eichinger, Sándor [Verfasser], and Frank [Akademischer Betreuer] Thiele. "Active flow separation control of ground transportation vehicle configurations / Sandor Eichinger. Betreuer: Frank Thiele." Berlin : Universitätsbibliothek der Technischen Universität Berlin, 2012. http://d-nb.info/1027184294/34.

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32

Jabbal, Mark. "Understanding the behaviour of synthetic jets in a boundary layer for flow separation control." Thesis, University of Manchester, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.504739.

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Forecasts in air traffic growth, coupled with increases in output of atmospheric carbon pollution, have placed greater demands on the aircraft manufacturing industry to pursue design optimisations that will minimise operating costs and improve aircraft efficiency. Internationally agreed goals, such as the European Vision for 2020 have been set to help alleviate the environmental impact of future aircraft. The development of active flow control technologies, consisting of dynamic actuators with the ability to respond to changes in now conditions at full-scale night, as opposed to the static nat
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33

Zhou, Jue. "Numerical investigation of the behaviour of circular synthetic jets for effective flow separation control." Thesis, University of Manchester, 2010. https://www.research.manchester.ac.uk/portal/en/theses/numerical-investigation-of-the-behaviour-of-circular-synthetic-jets-for-effective-flow-separation-control(6faae20e-82d6-4efb-8044-c02b089d667c).html.

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The stringing regulation on greenhouse gases emissions coupled with the rising fuel price and the growth in aviation transportation have imposed increasing demands on the aircraft industry to develop revolutionary technologies to meet such challenges. Methods of delaying flow separation on aircraft high lift systems have been sought which can lead to an increase in the aircraft performance and ultimately a reduction in aircraft operational costs and its impact on the environment. Synthetic jet actuators are a promising method of delivering flow control for aircraft applications due to their ab
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34

Guo, Fushui. "Experimental study of the behaviour of the synthetic jets for effective flow separation control." Thesis, University of Manchester, 2010. https://www.research.manchester.ac.uk/portal/en/theses/experimental-study-of-the-behaviour-of-the-synthetic-jets-for-effective-flow-separation-control(c05f07fb-e084-43ed-9d94-0745b7e8e69a).html.

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The increase in fuel price and the enforcement of more restrictive regulations have presented significant challenges to the aircraft industry and forced the development and implementation of revolutionary technologies so as to reduce operational costs and environmental impact of aircraft transportation. The development of active flow control is believed to be one of the key measures to meet these challenges.Synthetic jet actuators, as a promising method for flow separation control, are capable of injecting momentum to the external flow with zero-net-mass-flux, which negate the need for air sup
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35

Weier, Tom. "Elektromagnetische Strömungskontrolle mit wandparallelen Lorentzkräften in schwach leitfähigen Fluiden." Forschungszentrum Dresden, 2010. http://nbn-resolving.de/urn:nbn:de:bsz:d120-qucosa-28435.

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Die vorliegende Arbeit widmet sich der, vorwiegend experimentellen, Untersuchung der Wirkung wandparalleler Lorentzkräfte in Strömungsrichtung auf Grenzschichtprofile und Körperumströmungen. Die Themen - Beeinflussung der Grenzschicht an ebenen Platten mit stationären Lorentzkräften - Kontrolle von Strömungsablösungen an Zylindern und symmetrischen Profilen mit stationären Lorentzkräften - Beeinflussung von Zylindernachläufen und abgelösten Tragflügelumströmungen mit zeitlich periodischen Lorentzkräften werden behandelt.
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Weier, Tom. "Elektromagnetische Strömungskontrolle mit wandparallelen Lorentzkräften in schwach leitfähigen Fluiden." Forschungszentrum Rossendorf, 2006. https://hzdr.qucosa.de/id/qucosa%3A21670.

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Die vorliegende Arbeit widmet sich der, vorwiegend experimentellen, Untersuchung der Wirkung wandparalleler Lorentzkräfte in Strömungsrichtung auf Grenzschichtprofile und Körperumströmungen. Die Themen - Beeinflussung der Grenzschicht an ebenen Platten mit stationären Lorentzkräften - Kontrolle von Strömungsablösungen an Zylindern und symmetrischen Profilen mit stationären Lorentzkräften - Beeinflussung von Zylindernachläufen und abgelösten Tragflügelumströmungen mit zeitlich periodischen Lorentzkräften werden behandelt.
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37

Katam, Vamsidhar. "SIMULATION OF LOW-RE FLOW OVER A MODIFIED NACA 4415 AIRFOIL WITH OSCILLATING CAMBER." UKnowledge, 2005. http://uknowledge.uky.edu/gradschool_theses/339.

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Recent interest in Micro Aerial Vehicles (MAVs) and Unmanned Aerial Vehicles (UAVs) have revived research on the performance of airfoils at relatively low Reynolds numbers. A common problem with low Reynolds number flow is that separation is almost inevitable without the application of some means of flow control, but understanding the nature of the separated flow is critical to designing an optimal flow control system. The current research presents results from a joint effort coupling numerical simulation and wind tunnel testing to investigate this flow regime. The primary airfoil for these st
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38

Tessier, Frederic. "Modelling of electrokinetic phenomena involving confined polymers: Applications to DNA separation and electroosmotic flow control." Thesis, University of Ottawa (Canada), 2006. http://hdl.handle.net/10393/29321.

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Microfluidic and nanofluidic technology is revolutionizing experimental practices in analytical chemistry, molecular biology and medicine. Indeed, the development of systems of small dimensions for the processing of fluids heralds the miniaturization of traditional, cumbersome laboratory equipment onto robust, portable and efficient microchip devices (similar to the electronic microchips found in computers). Moreover, the conjunction of scale between the smallest man-made device and the largest macromolecules evolved by Nature is fertile ground for the blooming of our knowledge about the key p
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McQuilling, Mark. "EXPERIMENTAL STUDY OF ACTIVE SEPARATION FLOW CONTROL IN A LOW PRESSURE TURBINE BLADE CASCADE MODEL." UKnowledge, 2004. http://uknowledge.uky.edu/gradschool_theses/320.

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The flow field around a low pressure turbine (LPT) blade cascade model with and without flow control is examined using ejector nozzle (EN) and vortex generator jet (VGJ) geometries for separation control. The cascade model consists of 6 Pak-B Pratt andamp; Whitney low pressure turbine blades with Re = 30,000-50,000 at a free-stream turbulence intensity of 0.6%. The EN geometry consists of combined suction and blowing slots near the point of separation. The VGJs consist of a row of holes placed at an angle to the free-stream, and are tested at two locations of 69% and 10.5% of the suction surfa
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40

Zhang, Xue Feng. "Separation and transition control on ultra-high-lift low pressure turbine blades in unsteady flow." Thesis, University of Cambridge, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.613985.

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41

von, Stillfried Florian. "Computational studies of passive vortex generators for flow control." Licentiate thesis, KTH, Mechanics, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-11737.

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<p>Many flow cases in fluid dynamics face undesirable flow separation due torising static pressure on wall boundaries. This occurs e.g. due to geometry as ina highly curved turbine inlet duct or e.g. on flow control surfaces such as wingtrailing edge flaps within a certain angle of attack range. Here, flow controldevices are often used in order to enhance the flow and delay or even totallyeliminate flow separation. Flow control can e.g. be achieved by using passiveor active vortex generators (VG) that enable momentum mixing in such flows.This thesis focusses on passive VGs, represented by VG v
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42

Moore, Kenneth Jay Jr. "Large Scale Visualization of Pulsed Vortex Generator Jets." Wright State University / OhioLINK, 2005. http://rave.ohiolink.edu/etdc/view?acc_num=wright1133809534.

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43

Rinehart, Christopher S. "Aerodynamic forces induced by controlled transitory flow on a body of revolution." Diss., Georgia Institute of Technology, 2011. http://hdl.handle.net/1853/42830.

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The aerodynamic forces and moments on an axisymmetric body of revolution are controlled in a low-speed wind tunnel by induced local flow attachment. Control is effected by an array of aft-facing synthetic jets emanating from narrow, azimuthally segmented slots embedded within an axisymmetric backward facing step. The actuation results in a localized, segmented vectoring of the separated base flow along a rear Coanda surface and induced asymmetric aerodynamic forces and moments. The observed effects are investigated in both quasi-steady and transient states, with emphasis on parametric dependen
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44

Sirangu, Vijaya. "AERODYNAMIC CONTROL OF SLENDER BODIES AT HIGH ANGLES OF ATTACK." University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1271365316.

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45

Thake, Michael Patrick Jr. "Investigation of a Laminar Airfoil with Flow Control and the Effect of Reynolds Number." The Ohio State University, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=osu1292962211.

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46

Marks, Christopher R. "Surface Stress Sensors for Closed Loop Low Reynolds Number Separation Control." Wright State University / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=wright1309998636.

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47

Thompson, Andrew C. "Investigation and Simulation of Ion Flow Control over a Flat Plate and Compressor Cascade." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/33078.

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An investigation of ion flow control was performed to determine the effect of a positive, DC corona discharge on the boundary layer profile along a flat plate and to examine its ability to prevent separated flow in a low-speed compressor cascade. Flat plate tests were performed for two electrode configurations at free-stream velocity magnitudes of 2.5, 5, 7.5, and 10 m/s. Boundary layer velocity profile data was taken to measure the performance of the electrode pairs. Ion flow control was also tested in the compressor cascade for a stagger angle of 25° at angles of attack equal to 6° and
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48

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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49

Chard, James. "Tangential leading edge blowing for flow control on non-slender delta wings." Thesis, University of Manchester, 2018. https://www.research.manchester.ac.uk/portal/en/theses/tangential-leading-edge-blowing-for-flow-control-on-nonslender-delta-wings(0ed0f6fa-23ad-44a2-a187-e8e1e8f1ac8a).html.

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Abstract:
In the military arena there is an increase in demand for Low Observable (LO) flight vehicles. This drive for low observability imposes limits on Leading Edge (LE) sweep angles and prohibits the use of a tailplane/fin resulting in unconventional configurations; a typical example of which are Unmanned Combat Aerial Vehicles (UCAVs). This class of aircraft poses stability and control problems due to the early onset of flow separation. The focus of this project is on the on the use of Tangential Leading Edge Blowing (TLEB) as a means of separation suppression on such vehicles. This project is uniq
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50

Gan, Subhadeep. "Active Separation Control of High-Re Turbulent Separated Flow over a Wall-Mounted Hump using RANS, DES, and LES Turbulence Modeling Approaches." University of Cincinnati / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1275924069.

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