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Dissertations / Theses on the topic 'Wind tunnel testing'

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Published: 4 June 2021
Last updated: 25 July 2025

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1

Abrahamsen, Ida Sinnes. "Wind tunnel model testing of offshore platforms." Thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for energi- og prosessteknikk, 2012. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-18627.

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The purpose of this thesis is to highlight some of the areas of interest when it comes to wind tunnel experimenting of offshore platforms regarding stability concerns such as critical angles and wind overturning moment. Some important factors include design of tower geometry, the effect of surface roughness on drag, methods of calculating blockage corrections of wall interference and the generation of an atmospheric boundary layer to resemble full-scale conditions. Data obtained from wind tunnel experiments with two different models have been compared and discussed according to the areas of in
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2

Danis, Reed. "Investigating Forward Flight Multirotor Wind Tunnel Testing in a 3-by 4-foot Wind Tunnel." DigitalCommons@CalPoly, 2018. https://digitalcommons.calpoly.edu/theses/1909.

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Investigation of complex multirotor aerodynamic phenomena via wind tunnel experimentation is becoming extremely important with the rapid progress in advanced distributed propulsion VTOL concepts. Much of this experimentation is being performed in large, highly advanced tunnels. However, the proliferation of this class of vehicles extends to small aircraft used by small businesses, universities, and hobbyists without ready access to this level of test facility. Therefore, there is a need to investigate whether multirotor vehicles can be adequately tested in smaller wind tunnel facilities. A tes
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3

Kayisoglu, Bengi. "Investigation Of Wind Effects On Tall Buildings Through Wind Tunnel Testing." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12613324/index.pdf.

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In recent years, especially in the crowded city-centers where land prizes have become extremely high, tall buildings with more than 30 floors have started to be designed and constructed in Turkey. On the other hand, the technical improvements have provided the opportunity of design and construction of more slender structures which are influenced by the wind actions more. If the building is flexible, wind can interact with it so the wind induced oscillations can be significantly magnified. In order to analyze the response of such buildings under wind effects, wind tunnel tests are accepted to b
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4

Sheng, Wanan. "CFD simulations in support of wind tunnel testing." Thesis, University of Glasgow, 2003. http://theses.gla.ac.uk/5393/.

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CFD and wind tunnel simulations are complementary due to their inherent limitations. Wind tunnel tests apply to any hypothesis, but are limited by the tunnel wall interference/blockage, the model details, and even the distortion of the model. CFD are not limited in any of these ways, but limited in speed and memory and the lack of determinate set of equations. Theoretically, CFD can provide an assessment of any problem in fluid dynamics (Direct Numerical Simulation), but the requirements of speed and memory are far from being met presently, or even in the foreseeable future. Of necessity, pres
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Abudaram, Yaakov Jack. "Wind tunnel testing of load-alleviating membrane wings." [Gainesville, Fla.] : University of Florida, 2009. http://purl.fcla.edu/fcla/etd/UFE0041340.

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6

Hameury, Michel. "Development of the tolerant wind tunnel for bluff body testing." Thesis, University of British Columbia, 1987. http://hdl.handle.net/2429/27311.

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In conventional wind tunnels the solid-wall or open-jet test section imposes on the flow field around the test model new boundary conditions absent in free air. Unless a small model is used, the solid-wall test section generally increases the loadings on the model while the open-jet boundary decreases the loadings compared to the unconfined case. However, the development of a low wall-interference test section and its successful demonstration would allow the testing of relatively large models without the application of often uncertain correction formulae. The Tolerant wind tunnel, which makes
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7

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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8

Hetherington, Ben. "Interference of supports used for ground vehicle wind tunnel testing." Thesis, Durham University, 2006. http://etheses.dur.ac.uk/2671/.

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In order to provide a correct aerodynamic simulation of a vehicle travelling along the ground, models are tested using rotating wheels in a wind tunnel with a moving ground. In the most common of moving ground configurations the model is supported by an overhead strut, usually designed as an aerofoil profile to minimise interference, with the wheels supported by lateral stings hinged to mounts outside the span of the moving ground plane. ๒ using this type of configuration it is assumed that the presence of the intruding supports do not markedly affect the aerodynamic behaviour of the model, bu
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9

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

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10

Ratliff, Card. "Revitalization and initial testing of a blowdown supersonic wind tunnel." Master's thesis, Mississippi State : Mississippi State University, 2008. http://library.msstate.edu/etd/show.asp?etd=etd-07312008-093307.

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11

Joseph, Liselle AnnMarie. "Transition Detection for Low Speed Wind Tunnel Testing Using Infrared Thermography." Thesis, Virginia Tech, 2014. http://hdl.handle.net/10919/78145.

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Transition is an important phenomenon in large scale, commercial, wind tunnel testing at low speeds because it is an excellent indicator of an airfoil performance. It is difficult to estimate transition through numerical techniques because of the complex nature of viscous flow. Therefore experimental techniques can be essential. Over the transition region the rate of heat transfer shows significant increases which can be detected using infrared thermography. This technique has been used predominantly at high speeds, on small models made of insulated materials, and for short test runs. Large sc
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12

Garbutt, Keith Stuart. "Propulsion simulation in a magnetic suspension wind tunnel with special reference to force measurement." Thesis, University of Southampton, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336134.

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13

Malik, Abdullah. "Suppression of junction flow effects in half model wind tunnel testing." Thesis, Loughborough University, 2013. https://dspace.lboro.ac.uk/2134/11568.

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Half model testing is considered a valuable wind tunnel technique that offers many benefits over conventional full span testing. The technique suffers from aerodynamic losses due to flow separations on the model surfaces near the model/floor junction. Computational Fluid Dynamics, employing the Spalart-Allmaras turbulence model, and experimental investigations were carried out to evaluate the losses and to investigate the effect of localised suction on the junction flows. The wind tunnel model used was a rectangular and untwisted wing having a NASA LS(1)-0413 cross section and with a physical
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14

Neal, Graeme. "Three-dimensional model testing in the transonic self-streamlining wind tunnel." Thesis, University of Southampton, 1988. https://eprints.soton.ac.uk/52257/.

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The wall interference effects present on three-dimensional models during wind tunnel testing are difficult to correct using post-test model data correction methods. Further, at transonic speeds, with the use of ventilated test sections these corrections become complex to apply and inaccurate. The high quality of wind tunnel testing that is required today means that such methods are no longer satisfactory. The flexible walled wind tunnel has in recent years shown its ability to obtain two-dimensional aerofoil data free from the effects of wall boundary restraint. This work at Southampton was ai
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15

Saddington, Alistair J. "Mutual Interference Between Jets and Intakes in STOVL Aircraft." Thesis, Department of Aerospace, Power and Sensors, 2009. http://hdl.handle.net/1826/3895.

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During wind tunnel testing of jet-lift, short take-off and vertical landing (STOVL) aircraft it is usual to simulate the jet efflux but not the intake flows. The intakes, which are commonly faired over or are unpowered, are generally tested in separate wind tunnel experiments. The forces acting on the wind tunnel model are determined by the linear addition of the forces obtained from the two separate tests. There is some doubt as to whether this is a valid approach. A systematic experimental investigation was, therefore, conducted to determine the magnitude of any jet/intake interference effec
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16

Rosson, Joel Christopher. "Dynamic flow quality measurements in a transonic cryogenic wind tunnel." Thesis, Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/101463.

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Two instruments mounted in a piggyback arrangement were developed for time-resolved measurements of dynamic flow quality in a transonic cryogenic wind tunnel. The first one is a dual hot-wire aspirating probe for measurement of stagnation pressure and temperature. The second is a miniature high-frequency response angle probe consisting of surface mounted pressure sensors. The aspirating probe was tested in the 0.3-m Transonic Cryogenic Tunnel (TCT) at NASA-Langley Research Center. Stagnation pressure and temperature measurements were taken in the free-stream of the settling chamber and test
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17

Wiggs, Giles F. S. "Airflow over Barchan dunes : field measurements, mathematical modelling and wind tunnel testing." Thesis, University College London (University of London), 1992. http://discovery.ucl.ac.uk/1317535/.

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There are few empirical measurements of velocity, shear velocity, sand transport, morphological change on the windward slopes of dunes.This thesis compares field measurements on a barchan dune in Oman with calculations using a mathematical model (FLOWSTAR) and measurements in a wind tunnel. All three techniques demonstrate similar patterns of velocity, confirming the acceleration of flow up the windward slope, deceleration between the crest and brink and significant flow deceleration upwind of and at the toe of the dune. The FLOWSTAR model is unable accurately to predict airflow at the brink a
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18

Hyvärinen, Ann. "Investigation of blockage correction methods forfull-scale wind tunnel testing of trucks." Thesis, KTH, Flygdynamik, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-180436.

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In this work wall interference effects, experienced during full scale wind tunnel testing of trucks, are investigatedthrough simulations. Three different truck models are used, and a number of blockage correction methods areapplied on drag results from simulations in a wind tunnel environment. These are compared with open roadreference simulations. The results indicate that the flow fields around the trucks need to be fairly similar, if thesame correction method is to be used.
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19

Lehmkuehler, Kai. "A Direct Comparison of Small Aircraft Dynamics between Wind Tunnel and Flight Tests." Thesis, The University of Sydney, 2016. http://hdl.handle.net/2123/16511.

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The miniaturization of embedded electronics and sensors driven by the rapid development of mobile devices has enabled powerful avionics systems for very small aircraft. This enables a potential step forward in accurate flight data gathering for vehicles weighing 5 kg or less. Being able to flight test a small platform like this also allows the comparison of the results with reference data from ground testing in a standard sized wind tunnel of an identical airframe. With this process, the following questions can be answered: Firstly, would such a system then be able to collect accurate flight d
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20

Zientarski, Lauren Ann. "Wind Tunnel Testing of a Variable Camber Compliant Wing with a Unique Dual Load Cell Test Fixture." University of Dayton / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1448893315.

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21

Cedrun, Mark E. "Low-speed wind tunnel testing of the NPS/NASA Ames Mach 6 optimized waverider." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1994. http://handle.dtic.mil/100.2/ADA283585.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, June 1994.<br>Thesis advisor(s): Conrad F. Newberry, Jeffrey V. Bowles. "June 1994." Includes bibliographical references. Also available online.
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22

Talon, Ludovic 1976. "Development of a biofeedback system for optimizing cycling performance assessment during wind tunnel testing." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/82259.

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23

Pereira, Jason L. "Hover and wind-tunnel testing of shrouded rotors for improved micro air vehicle design." College Park, Md.: University of Maryland, 2008. http://hdl.handle.net/1903/8752.

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Thesis (Ph. D.) -- University of Maryland, College Park, 2008.<br>Thesis research directed by: Dept. of Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.
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24

Broughton, Benjamin Albert. "Low speed wind tunnel testing and data correction methods for aircraft models in ground effect." Diss., University of Pretoria, 1999. http://hdl.handle.net/2263/24292.

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In this thesis, techniques for testing aircraft models in ground effect in a low speed wind tunnel are investigated. Although these types of tests have been done before, the current study is unique in that forces are measured with an overhead balance instead of an internal balance. This has the advantage that the types of models that are difficult to mount on a sting with an internal balance, can often be mounted with a strut protruding from the top of the model. Positioning a sting-mounted model close to the ground at a high angle-of-attack is also usually difficult if not impossible. Finally
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25

Broughton, Cabot A. Carleton University Dissertation Engineering Aeronautical. "Experimental investigation of slotted wall wind tunnel test sections for low interference road vehicle testing." Ottawa, 1990.

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26

Montero, Ryan M. "Analysis, Design and Testing of a Wind Tunnel Model to Validate Fiber-Optic Shape Sensing Systems." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/23233.

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The ability to collect valuable data concerning the stress, strains, and shape profiles of aircraft and aircraft components during flight is important to fields such as structural health monitoring, gust alleviation, and flutter control. A research interest in the form of a NASA Phase<br />I SBIR called for possible systems that would be able to take accurate shape sensing data on a flexible wing aircraft. In a joint venture between Luna Technologies Inc. and Virginia<br />Polytechnic Institute and State University a flexible wing wind tunnel model was designed and constructed as a test articl
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27

Carlsson, Martin. "Design and Testing of Flexible Aircraft Structures." Doctoral thesis, KTH, Aeronautical and Vehicle Engineering, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3761.

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<p>Methods for structural design, control, and testing offlexible aircraft structures are considered. Focus is onnonconventional aircraft con- figurations and control concepts.The interaction between analysis and testing is a central topicand all studies include validation testing and comparisonbetween computational and experimental results.</p><p>The first part of the thesis is concerned with the designand testing of an aeroelastic wind-tunnel model representing aBlended Wing Body (BWB) aircraft. The investigations show thata somewhat simplified wind-tunnel model design concept isuseful and e
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28

Horton, Damien. "Development of an Infrared Thermography System to Measure Boundary Layer Transition in a Low Speed Wind Tunnel Testing Environment." DigitalCommons@CalPoly, 2021. https://digitalcommons.calpoly.edu/theses/2287.

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The use of infrared thermography for boundary layer detection was evaluated for use in the Cal Poly Low Speed Wind Tunnel (LSWT) and recommendations for the successful use of this technique were developed. In cooperation with Joby Aviation, an infinite wing model was designed, manufactured and tested for use in the LSWT. The wing was designed around a custom airfoil profile specific for this project, where the nearly-flat pressure gradient at a zero pitch angle would delay the chordwise onset of boundary layer transition. Steady-state, RANS numerical simulations predicted the onset of transiti
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29

Sholtis, Paul M. "Characterization of Upstream Effects Due to High Blockage in the AFRL Vertical Wind Tunnel." University of Dayton / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=dayton155594746187138.

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30

Miranda, Sergio. "Active Control of Separated Flow over a Circular-Arc Airfoil." Thesis, Virginia Tech, 2000. http://hdl.handle.net/10919/34411.

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An experimental study of active control of fully separated flow over a symmetrical circular-arc airfoil at high angles of attack was performed. The experiments were carried out in a low-speed, open circuit wind tunnel. Angles of attack from 10 to 40 degrees were tested. Low-power input, unsteady excitation was applied to the leading or trailing edge shear layers. The actuation was provided by the periodic oscillation of a 4-percent-chord flap placed on the suction side of the airfoil and facing the sharp edge. Vortex-shedding frequencies were measured and harmonic combinations selected as the
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31

Heim, Eugene Henry DeWendt. "Development of Methods for Improved Data Integrity and Efficient Testing of Wind Tunnel Models for Dynamic Test Conditions in Unsteady and Nonlinear Flight Regimes." Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/31050.

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Todayâ s high performance aircraft are operating in expanded flight envelopes, often maneuvering at high angular rates at high angles-of-attack, even above maximum lift. Current aerodynamic models are inadequate in predicting flight characteristics in the expanded envelope, such as rapid aircraft departures and other unusual motions. Unsteady flows of aircraft are of real concern. The ability to accurately measure aerodynamic loads directly impacts the ability to accurately model and predict flight. Current wind tunnel testing techniques do not adequately address the data fidelity of a test p
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Taylor, Nigel John. "Adaptive wall technology for two-dimensional wind tunnel testing at high subsonic through to low supersonic speeds." Thesis, University of Southampton, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.294622.

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33

Sevier, Abigail. "Feasibility Study for Testing the Dynamic Stability of Blunt Bodies with a Magnetic Suspension System in a Supersonic Wind Tunnel." Case Western Reserve University School of Graduate Studies / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=case1493207020743959.

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34

Child, Malcolm S. (Malcolm Swope). "The design, fabrication, and testing of a wind tunnel for the study of the turbulent transport of aerosols." Thesis, Massachusetts Institute of Technology, 1992. http://hdl.handle.net/1721.1/39361.

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35

Ng, Eton Yat-Tuen, and eton_ng@hotmail com. "Vehicle engine cooling systems: assessment and improvement of wind-tunnel based evaluation methods." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2002. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080422.100014.

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The high complexity of vehicle front-end design, arising from considerations of aerodynamics, safety and styling, causes the airflow velocity profile at the radiator face to be highly distorted, leading to potentially reduced airflow volume for heat dissipation. A flow visualisation study showed that the bumper bar significantly influenced the cooling airflow, leading to three-dimensional vortices in its wake and generating an area of relatively low velocity across at least one third of the radiator core. Since repeatability and accuracy of on-road testing are prejudiced by weather condit
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Unal, Sadullah Utku. "Design, Construction And Preliminary Testin Of An Aeroservoelastic Test Apparatus To Be Used In Ankara Wind Tunnel." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/12607034/index.pdf.

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In this thesis, an aeroservoelastic test appratus is designed to investigate the flutter phenomena in a low speed wind tunnel environment. Flutter is an aeroelastic instability that may occur at control surfaces of aircrafts and missiles. Aerodynamic, elastic, and inertial forces are involved in flutter. A mathematical model using aeroelastic equations of motion is derived to investigate flutter and is used as a basis to design the test setup. Simulations using this mathematical model are performed and critical flutter velocities and frequencies are found. Stiffness characteristics of the test
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Edwards, Alex T. "Comparison of Strain Gage and Fiber Optic Sensors On A Sting Balance In A Supersonic Wind Tunnel." Thesis, Virginia Tech, 2000. http://hdl.handle.net/10919/30799.

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Force and moment balances have proved to be essential in the measurement and calculation of aerodynamic properties during wind tunnel testing. With the recent advancements of technology, new fiber optic sensors have been designed to replace the conventional foil strain gage sensors commonly found on balances, thereby offering several distinct advantages. The use of fiber optic sensors on a balance brings with it some potential advantages over conventional strain gage balances including increased resolution and accuracy, insensitivity to electromagnetic interference, and the capability of use
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Stephens, Arthur William, and arthur stephens esb ie. "Aerodynamic Cooling of Automotive Disc Brakes." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2006. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20070108.121737.

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Sufficient heat dissipation is crucial to the effective operation of friction based braking systems. Such cooling is generally provided by ensuring a sufficient supply of cooling air to the heated components, hence the aerodynamics in the region of the brake components is extremely important. The objective of the research was to develop an understanding of how aerodynamics could be used to improve the cooling of automotive disc brakes. Two separate sets of wind tunnel experiments were developed. Tests were performed on a vented disc (rotor) to measure the internal flow through the
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Pinn, Jarred Michael. "Effect of End-Plate Tabs on Drag Reduction of a 3D Bluff Body with a Blunt Base." DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/698.

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This thesis involves the experimental testing of a bluff body with a blunt base to evaluate the effectiveness of end-plate tabs in reducing drag. The bluff body is fitted with interchangeable end plates; one plate is flush with the rest of the exterior and the other plate has small tabs protruding perpendicularly into the flow. The body is tested in the Cal Poly 3ft x 4ft low speed wind tunnel. Testing is conducted in three phases. The first phase was the hot-wire measurement of streamwise velocity of the near wake behind the bluff body. An IFA300 thermal anemometry system with a hot-wire prob
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Fu, Tuan-Chun. "Development of Effective Approaches to the Large-Scale Aerodynamic Testing of Low-Rise Building." FIU Digital Commons, 2013. http://digitalcommons.fiu.edu/etd/986.

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Low-rise buildings are often subjected to high wind loads during hurricanes that lead to severe damage and cause water intrusion. It is therefore important to estimate accurate wind pressures for design purposes to reduce losses. Wind loads on low-rise buildings can differ significantly depending upon the laboratory in which they were measured. The differences are due in large part to inadequate simulations of the low-frequency content of atmospheric velocity fluctuations in the laboratory and to the small scale of the models used for the measurements. A new partial turbulence simulation metho
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Rainbird, John. "Blockage tolerant wind tunnel testing of aerofoils at angles of incidence from 0 to 360 degrees, with respect to the self-start of vertical-axis wind turbines." Thesis, Imperial College London, 2016. http://hdl.handle.net/10044/1/61575.

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The need for better quality aerofoil data, extending to incidences well beyond stall, for the modelling of vertical-axis wind turbine (VAWT) start-up is established through blade element-momentum modelling. The model is used to show that differences between existing post-stall data are large enough to impact on turbine performance. The differences between the existing aerofoil data are found to result primarily from inconsistencies introduced by wind tunnel blockage and the potential flow-derived formulae used to correct for it. A blockage tolerant wind tunnel test section has been constructed
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Pickhaver, T. W. "Prediction and validation of the aerodynamic effects of simulated battle damage on aircraft wings." Thesis, Loughborough University, 2014. https://dspace.lboro.ac.uk/2134/14688.

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Aerodynamic analysis is an important area of survivability studies. There is a desire to be able to predict the aerodynamic effects of a given damage scenario on an aircraft wing with minimal wind tunnel testing or computational simulations. Due to the limited nature of previous studies, this has not generally been possible. The original contribution of this thesis is a predictive technique developed to estimate the aerodynamic effects of a simulated battle damage hole on an aircraft wing, resulting from a range of attack directions. This technique was successfully validated against experiment
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43

Johnson, Daniel Kenneth. "The Design and Implementation of a Supersonic Indraft Tube Wind Tunnel for the Demonstration of Supersonic Flows." DigitalCommons@CalPoly, 2018. https://digitalcommons.calpoly.edu/theses/1862.

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Historically, the endeavor of scale testing flight vehicles at supersonic Mach numbers, especially for long durations, has required the development of closed-loop wind tunnels, which are extremely expensive both to build and operate due to the high complexity and incredible power required to drive such a system. The intermittent blowdown wind tunnel, indraft tunnel, and shock tunnel have alleviated many of these cost requirements to some degree, whilst facilitating testing at very high Mach numbers and enthalpies; however, these systems require the handling of gases at pressures and temperatur
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Miller, Ryan R. "A SYSTEM FOR MEASURING THE LIFT AND DRAG FORCES OF A SPINNING GOLF BALL HELD FIXED WITHIN A WIND TUNNEL." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/44.

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A system was designed, built and tested in order to test the aerodynamic properties of a standard golf ball in a wind tunnel manufactured by ELD, Inc. model 406(B). The system consists of a rotating shaft, on which the golf ball is attached, connected to a two-axis force transducer. Additionally, an automated data acquisition system was built for enhanced precision of measurements. Data for wind speeds up to 160 ft/s and rotational speeds up to 8,600 rpm were obtained and analyzed. The purpose of the designed apparatus was to allow for studies to better understand the lift and drag coeffic
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Kim, Daeung. "The Application of CFD to Building Analysis and Design: A Combined Approach of an Immersive Case Study and Wind Tunnel Testing." Diss., Virginia Tech, 2014. http://hdl.handle.net/10919/25140.

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Computational Fluid Dynamics (CFD) can play an important role in building design. For all aspects and stages of building design, CFD can be used to provide more accurate and rapid predictions of building performance with regard to air flow, pressure, temperature, and similar parameters. Generally, the process involved in conducting CFD analyses is relatively complex and requires a good understanding of how best to utilize computational numerical methods. Moreover, the level of skill required to perform an accurate CFD analysis remains a challenge for many professionals particularly architec
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Pierce, Warrick Tait. "Evaluation and performance prediction of a wind turbine blade." Thesis, Stellenbosch : University of Stellenbosch, 2009. http://hdl.handle.net/10019.1/1791.

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Thesis (MScEng (Mechanical and Mechatronic Engineering))--University of Stellenbosch, 2009.<br>The aerodynamic performance of an existing wind turbine blade optimised for low wind speed conditions is investigated. The aerodynamic characteristics of four span locations are determined from surface pressure measurements and wake surveys with a traversed five-hole probe performed in a low speed wind tunnel for chord Reynolds numbers ranging from 360,000 - 640,000. Two-dimensional modelling of the wind tunnel tests is performed with the commercial computational fluid dynamics code FLUENT. The
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Li, Ruilong. "Effects of Architectural Features of Air-Permeable Roof Cladding Materials on Wind-Induced Uplift Loading." FIU Digital Commons, 2012. http://digitalcommons.fiu.edu/etd/659.

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Widespread damage to roofing materials (such as tiles and shingles) for low-rise buildings, even for weaker hurricanes, has raised concerns regarding design load provisions and construction practices. Currently the building codes used for designing low-rise building roofs are mainly based on testing results from building models which generally do not simulate the architectural features of roofing materials that may significantly influence the wind-induced pressures. Full-scale experimentation was conducted under high winds to investigate the effects of architectural details of high profile roo
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48

Chen, Ru-Ching. "Development of a Supersonic Nozzle and Test Section for use with a Magnetic Suspension System for Re-Entry Aeroshell Models." Case Western Reserve University School of Graduate Studies / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=case1544179612537658.

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49

Cruz, Juan Ramón. "An Application of Anti-Optimization in the Process of Validating Aerodynamic Codes." Diss., Virginia Tech, 2003. http://hdl.handle.net/10919/26960.

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An investigation was conducted to assess the usefulness of anti-optimization in the process of validating of aerodynamic codes. Anti-optimization is defined here as the intentional search for regions where the computational and experimental results disagree. Maximizing such disagreements can be a useful tool in uncovering errors and/or weaknesses in both analyses and experiments. The codes chosen for this investigation were an airfoil code and a lifting line code used together as an analysis to predict three-dimensional wing aerodynamic coefficients. The parameter of interest was the maxi
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50

Lopes, Igor Moreira. "EVALUATION OF TRANSITIONS FOR TESTING AGRICULTURAL VENTILATION FANS WITH THE FAN ASSESSMENT NUMERATION SYSTEM (FANS)." UKnowledge, 2012. http://uknowledge.uky.edu/bae_etds/8.

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The Fan Assessment Numeration System (FANS) is an improved air velocity traverse method for measuring in situ fan performance. The FANS has been widely used, but variations of its test procedure are commonly employed to accommodate physical or operational barriers encountered in the field. This laboratory study evaluated the use of transitions to connect a 1.37m FANS unit to two smaller fans (1.22m and 0.91m diameter) and one 1.37m diameter fan. Tests were conducted with the FANS unit positioned on both intake and discharge sides of the fans. Three different transition angles (30o, 45o and 60o
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