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dc.contributor.authorBoutilier, Michael Stephen Hatcher 19:45:29 (GMT) 19:45:29 (GMT)
dc.description.abstractShear layer development over a NACA 0018 airfoil at a chord Reynolds number of 100,000 was investigated experimentally. The effects of experimental setup and analysis tools on the results were also examined. The sensitivity of linear stability predictions for measured separated shear layer velocity profiles to both the analysis approach and experimental data scatter was evaluated. Analysis approaches that are relatively insensitive to experimental data scatter were identified. Stability predictions were shown to be more sensitive to the analysis approach than to experimental data scatter, with differences in the predicted maximum disturbance growth rate and corresponding frequency of approximately 35% between approaches. A parametric study on the effects of experimental setup on low Reynolds number airfoil experiments was completed. It was found that measured lift forces and vortex shedding frequencies were affected by the end plate configuration. It was concluded that the ratio of end plate spacing to projected model height should be at least seven, consistent with the guideline for circular cylinders. Measurements before and after test section wall streamlining revealed errors in lift coefficients due to blockage as high as 9% and errors in the wake vortex shedding frequency of 3.5%. Shear layer development over the model was investigated in detail. Flow visualization images linked an observed asymmetry in wake velocity profiles to pronounced vortex roll-up below the wake centerline. Linear stability predictions based on the mean hot-wire profiles were found to agree with measured disturbance growth rates, wave numbers, and streamwise velocity fluctuation profiles. Embedded surface pressure sensors were shown to provide reasonable estimates of disturbance growth rate, wave number, and convection speed for conditions at which a separation bubble formed on the airfoil surface. Convection speeds of between 30 and 50% of the edge velocity were measured, consistent with phase speed estimates from linear stability theory.en
dc.publisherUniversity of Waterlooen
dc.subjectlow Reynolds number airfoilen
dc.subjectseparation bubbleen
dc.subjectNACA 0018 airfoilen
dc.subjectlaminar-to-turbulent transitionen
dc.subjectexperimental fluid mechanicsen
dc.subjectlaminar flow stabilityen
dc.subjectembedded surface pressure sensorsen
dc.subjectend platesen
dc.subjectadaptive-wall wind tunnelen
dc.subjecttest section blockageen
dc.titleExperimental Investigation of Transition over a NACA 0018 Airfoil at a Low Reynolds Numberen
dc.typeMaster Thesisen
dc.comment.hiddenPortions of Chapters 4, 5, and 6 have been published in the proceedings of the AIAA Fluid Dynamics Conference and Exhibit in 2010 and 2011. The publisher does not require me to obtain their written permission to publish this material in my thesis. Citations for the published conference papers are provided below, and I have received permission from my supervisor, the copyright holder on these papers, to publish the work in my thesis: (1) Boutilier, M. S. H. and Yarusevych, S. Inviscid Spatial Linear Stability Analysis of Separated Shear Layers based on Experimental Data. AIAA Paper No. 2010-4293. From the 40th Fluid Dynamics Conference and Exhibit, 28 June - 1 July 2010, Chicago, Illinois; (2) Boutilier, M. S. H. and Yarusevych, S. Effects of End Plates and Blockage on a Low Reynolds Number Airfoil Experiment. AIAA Paper No. 2011-3723. From the 41st Fluid Dynamics Conference and Exhibit, 27 - 30 June 2011, Honolulu, Hawaii; (3) Yarusevych, S. and Boutilier, M. S. H. Vortex Shedding Characteristics of a NACA 0018 Airfoil at Low Reynolds Numbers. AIAA Paper No. 2010-4628. From the 40th Fluid Dynamics Conference and Exhibit, 28 June - 1 July 2010, Chicago, Illinois.en
dc.subject.programMechanical Engineeringen and Mechatronics Engineeringen
uws-etd.degreeMaster of Applied Scienceen

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