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Explaining Chemical Reactions On the Use of Active Flow Control to Trim and Control a Tailles Aircraft Model Item Type text; Electronic Thesis Authors Jentzsch, Marvin Patrick Publisher The University of Arizona. Rights Copyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author. Download date 07/10/2021 06:46:41 Link to Item http://hdl.handle.net/10150/625917 ON THE USE OF ACTIVE FLOW CONTROL TO TRIM AND CONTROL A TAILLES AIRCRAFT MODEL by Marvin Jentzsch ____________________________ Copyright Marvin Jentzsch 2017 A Thesis Submitted to the Faculty of the DEPARTMENT OF AEROSPACE AND MECHANICAL ENGINEERING In Partial Fulfillment of the Requirements For the Degree of MASTER OF SCIENCE WITH A MAJOR IN AEROSPACE ENGINEERING In the Graduate College THE UNIVERSITY OF ARIZONA 2017 2 STATEMENT BY AUTHOR The thesis titled On the Use of Active Flow Control to Trim and Control a Tailless Aircraft Model prepared by Marvin Jentzsch has been submitted in partial fulfillment of requirements for a master’s degree at the University of Arizona and is deposited in the University Library to be made available to borrowers under rules of the Library. Brief quotations from this thesis are allowable without special permission, provided that an accurate acknowledgement of the source is made. Requests for permission for extended quotation from or reproduction of this manuscript in whole or in part may be granted by the head of the major department or the Dean of the Graduate College when in his or her judgment the proposed use of the material is in the interests of scholarship. In all other instances, however, permission must be obtained from the author. SIGNED: Marvin Jentzsch APPROVAL BY THESIS DIRECTOR This thesis has been approved on the date shown below: August 14, 2017 Israel Wygnanski Date Professor of Aerospace and Mechanical Engineering 3 Acknowledgement First and foremost I would like to thank my advisor Dr. Israel Wygnanski. His expertise and passionate guidance helped me in all aspects of my research and in writing my thesis. The support I have received from Dr. Wygnanski is more than I can put into words. He has never failed to encourage me to do more and strive for the best. His efforts made my dream of studying abroad possible. Furthermore, ‘Wygy’ was more than just professor to me and I am endlessly grateful for all things he did for me. Dr. Wygnanski will always have my upmost respect, thank you ‘Wygy’. I also would like to thank Lutz Taubert for his contributions towards the model design and necessary parts for conducting the experiments. His help in the laboratory and the knowledge he has provided me with is greatly appreciated. All members of the machine shop: Joe, Dale, Lane and Jason. Thank you for your all your help. It was a pleasure to bike up the “A” mountain with Joe to free up my mind. I thank all members (and former ones) of the Aerolab, Philipp Tewes, Emile Suehiro, Matt Sybrant, Shane Harrel, Elisa Phillips, and Harshard Kalyankar, for taking the time to help me set up experiment’s etc.. I enjoyed hearing all of your experiences and I gained from your knowledge in many theoretical, experimental and computational aspects. Additionally, I am grateful for having such a great research and classmate Harshad Kalyankar with whom I completed most of my classes throughout the time at the University of Arizona. Emile Suehiro with whom I also became roommates. Thank you for your help in and outside the lab. Your opinion about work and lifestyle changed my point of view in some aspects for the better. I joyfully look back to the times we went trout fishing to refresh our minds. Thank you to all of my friends who supported me and helped me clear my mind when needed. Creating this balance was important in my completion. I would also like to thank AFOSR (Grant Number FA 9550-14-0326) for sponsoring the project that was monitored by Dr. D. Smith. I also would like to thank my girlfriend Taylor. I don’t know how far I would have made it without your support. I appreciate your patience and understanding whenever I was working on weekends and/or late nights. You have always been there for me and I could always count on you. You are my person and I love you. 4 Last but not least I am extremely thankful for the support I have received from my family throughout the entire time here in the United States. I am so grateful for my parents Gabi and Jörg who have always supported me in everything I do. Your endless support gives me the necessary strength and security in life. You made me the person I am today and I cannot thank you enough. Table of Contents List of Figures ................................................................................................................................. 7 List of Tables ................................................................................................................................ 10 Nomenclature ................................................................................................................................ 11 Abstract ………………………………………………………………………………………………………………………...13 1. Introduction .................................................................................................................... 14 1.1. Sweepback ...................................................................................................................... 15 1.2. Separation/ Tip Stall/ Vortices ....................................................................................... 19 1.3. Wing Fence .................................................................................................................... 26 1.4. Static Stability ................................................................................................................ 28 1.5. Fluidic Oscillator ............................................................................................................ 30 1.5.1. Working Principle ................................................................................................... 31 1.5.2. Parameters affecting the sweeping motion ............................................................. 33 1.6. Active Flow Control (Interaction with Boundary Layer) ............................................... 35 1.7. Boundary Layer Independence Principle ....................................................................... 37 1.8. Pressure Sensitive Paint (PSP) ....................................................................................... 42 1.8.1. PSP Basic Principle................................................................................................. 42 1.8.2. Binary PSP .............................................................................................................. 45 2. Experimental Setup, Instrumentation and Data Acquisition .......................................... 47 2.1. Wind-tunnel and balance ................................................................................................ 47 2.2. Semi-span model: SACCON .......................................................................................... 48 2.3. PSP Setup ....................................................................................................................... 51 3. Results and Discussion ................................................................................................... 53 3.1. Trimming the airplane .................................................................................................... 53 3.2. Baseline observations without AFC ............................................................................... 55 3.3. Wing Fences ................................................................................................................... 61 3.4. Flap deflection ................................................................................................................ 66 3.5. Trailing Edge Actuation ................................................................................................. 68 3.5.1. 13TE evenly spaced ................................................................................................ 68 3.5.2. 4TE and 2TE evenly spaced ................................................................................... 75 3.6. Leading Edge Actuation ................................................................................................. 76 3.6.1. The Use of jets ........................................................................................................ 76 6 3.6.2. The Use of suction .................................................................................................. 81 3.7. Combined TE & LE Actuation....................................................................................... 83 3.8. Comparison of AFC and control surface deflection....................................................... 85 3.8.1. Yawing Moment ..................................................................................................... 86 3.8.2. Rolling Moment ...................................................................................................... 89 3.9. Combination of AFC and control surface deflection ..................................................... 91 3.10. Interaction of AFC and sweepback ...........................................................................
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