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dc.contributor.authorWexler, Chloe
dc.contributor.otherQueen's University (Kingston, Ont.). Theses (Queen's University (Kingston, Ont.))en
dc.date2014-08-07 09:45:40.365en
dc.date2014-08-08 16:31:57.799en
dc.date.accessioned2014-08-11T19:42:36Z
dc.date.available2014-08-11T19:42:36Z
dc.date.issued2014-08-11
dc.identifier.urihttp://hdl.handle.net/1974/12354
dc.descriptionThesis (Master, Mechanical and Materials Engineering) -- Queen's University, 2014-08-08 16:31:57.799en
dc.description.abstractThe undisturbed flow behavior in the Queen’s University Low Speed Wind Tunnel was investigated experimentally and computationally. The velocity profiles, turbulent parameters, boundary layer and corner effects were detailed by traversing the lower left quadrant of the wind tunnel with a seven-hole pressure probe and uniaxial constant temperature hot-wire anemometer. The research goal was to provide a complete reference data set as a comparison standard for future experimental work. The flow in the wind tunnel was verified using computational fluid dynamics in order to present the model requirements and inlet conditions required to accurately simulate the flow. The experimental results indicated that the LSWT was capable of producing a mean axial flow speed of 30 – 31 m/s, dependent on ambient conditions and atmospheric wind speeds, in a 1 m2 test section. Measurements were collected under a variety of external weather conditions and it was determined that the average transient and spatial flow deviation from the mean was on the order of 1.5% and 0.5% respectively. The boundary layer thickness at the exit of the test section was found to be 10 cm above the floor and the corner effects were determined to extend 15 cm into the test section. The turbulent intensity reached 10% at the wall boundaries decaying to a constant uniform value of 3% in the center. Computational simulations were performed for three specific sets of experimental data. The results indicated that the mean axial velocity was predicted with an average deviation of 0.5%. Solution results were extrapolated 1 m downstream from the contraction exit plane, averaged and used to provide reference inlet conditions to a simplified test section model. The turbulence model applied to the solution was varied; the Spalart-Allmaras, k-ε, k-ω, and the blended k-ω SST models were able to resolve the turbulent distribution and flow behavior in a comparable manner. The flow was predicted within the bounds of engineering accuracy, the discrepancy in the simulated and experimental mean velocity ranged from 0.4% to 0.02%.en_US
dc.languageenen
dc.language.isoenen_US
dc.relation.ispartofseriesCanadian thesesen
dc.rightsThis publication is made available by the authority of the copyright owner solely for the purpose of private study and research and may not be copied or reproduced except as permitted by the copyright laws without written authority from the copyright owner.en
dc.subjectLow Speed Wind Tunnelen_US
dc.subjectComputational Fluid Dynamicsen_US
dc.titleEXPERIMENTAL MEASUREMENT AND COMPUTATIONAL SIMULATION OF THE FLOW IN THE QUEEN’S UNIVERSITY LOW SPEED WIND TUNNELen_US
dc.typeThesisen_US
dc.description.degreeMasteren
dc.contributor.supervisorBirk, Michael A.en
dc.contributor.departmentMechanical and Materials Engineeringen


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