Aerodynamic Optimization for Low Reynolds Number Flight of a Solar Unmanned Aerial Vehicle
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UNLV Retrospective Theses & Dissertations 1-1-2008 Aerodynamic optimization for low Reynolds number flight of a solar unmanned aerial vehicle Louis Dube University of Nevada, Las Vegas Follow this and additional works at: https://digitalscholarship.unlv.edu/rtds Repository Citation Dube, Louis, "Aerodynamic optimization for low Reynolds number flight of a solar unmanned aerial vehicle" (2008). UNLV Retrospective Theses & Dissertations. 2398. http://dx.doi.org/10.25669/ziey-32pi This Thesis is protected by copyright and/or related rights. It has been brought to you by Digital Scholarship@UNLV with permission from the rights-holder(s). You are free to use this Thesis in any way that is permitted by the copyright and related rights legislation that applies to your use. For other uses you need to obtain permission from the rights-holder(s) directly, unless additional rights are indicated by a Creative Commons license in the record and/ or on the work itself. This Thesis has been accepted for inclusion in UNLV Retrospective Theses & Dissertations by an authorized administrator of Digital Scholarship@UNLV. For more information, please contact [email protected]. AERODYNAMIC OPTIMIZATION FOR LOW REYNOLDS NUMBER FLIGHT OF A SOLAR UNMANNED AERIAL VEHICLE by Louis Dube Bachelor of Science University of Nevada, Las Vegas 2006 A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science Degree in Aerospace Engineering Department of Mechanical Engineering Howard R. Hughes College of Engineering Graduate College University of Nevada, Las Vegas December 2008 UMI Number: 1463501 INFORMATION TO USERS The quality of this reproduction is dependent upon the quality of the copy submitted. Broken or indistinct print, colored or poor quality illustrations and photographs, print bleed-through, substandard margins, and improper alignment can adversely affect reproduction. 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Eisenhower Parkway PC Box 1346 Ann Arbor, Ml 48106-1346 Thesis Approval The Graduate College University of Nevada, Las Vegas November 21.2008 The Thesis prepared by Louis Philippe Dube Entitled Aerodynamic Optimization for Low Reynolds Number Flight of a Solar Unmanned Aerial Vehicle is approved in partial fulfillm ent of the requirements for the degree of Master of Science in Aerospace Engineering _____ Examination Committee Chair Dean o f the Graduate College Examination Committee Member Examination Committee Member Graduate College Faculty Representative 11 ABSTRACT Aerodynamic Optimization for Low Reynoids Number Fiight of a Solar Unmanned Aerial Vehicle By Louis Dube Dr. Darrell Pepper, Examination Committee Chair Professor of Mechanical Engineering University of Nevada, Las Vegas A study has been conducted to optimize the aerodynamics of a solar powered unmanned aerial vehicle for low Reynolds number flight, in this study, three areas of the airframe, namely the fuselage, wing-fuselage junction and wingtips, were analyzed, tested, evaluated and developed in an iterative design process. A numérisai analysis method was employed to complete the aerodynamic study, the purpose of which was to minimize adverse flow conditions occurring near or about the aforementioned areas under most fiight conditions and to maximize their aerodynamic usefulness. The results were benchmarked internally through the iterative process using the initiai design as a control and externally by comparing with collected empirical figures characterizing solar airplanes of the past and present. The results showed that with carefui design practices, wingtip devices can be made to improve flight characteristics at low Reynolds number flight significantly enough to offset their structurai disadvantages, providing a substantial drag decrease over the entire flight envelope. It was also shown that fuselage shape can be modified to accommodate the airplane’s mission and fulfili a greater role than solely being a payload carrier by using this body to generate and control aerodynamic forces. Finally it was illustrated that careful design of the wing-fuselage junction could lead to significant improvements in both lift and drag characteristics. TABLE OF CONTENTS ABSTRACT............................................................................................................................................. Hi LIST OF TABLES...................................................................................................................................vll LIST OF FIGURES.................................................................................................................................. x NOMENCLATURE................................................................................................................................xiii ACKNOWLEDGEMENTS....................................................................................................................xiv CHAPTER 1 INTRODUCTION........................................................................................................... 1 1.1 General Information ................................................................................................................ 1 1.2 Motivation ................................................................................................................................ 5 1.3 Problem Description ............................................................................................................... 7 CHAPTER 2 LiTERATURE SURVEY................................................................................................ 8 2.1 Wingtip Devices - History and Research .............................................................................8 2.2 Fuselage - History and Research ....................................................................................... 12 2.3 Wing-Fuselage Junction - History and Research ................................................... 13 CHAPTER 3 SET-UP AND PROCEDURE............................................................................... 17 3.1 Introduction ................................. 17 3.2 Winglet and Wingtip Design Parameters ............................................................................ 17 3.3 Fuselage and Wing-Fuselage Junction Design Parameters ..............................................20 3.4 Resources .............................................................................................................................22 3.5 Model Set-Ups ............................................................................................................23 3.5.1 Computational Method ................................................................................................24 3.5.2 Computational Domain Modeiing ...............................................................................30 3.5.3 Other Considerations Regarding the Computational Domain ................................ 32 3.6 Test Section Calibration .......................................................................................................32 CHAPTER 4 WINGTiP DEVICE SIMULATION ANALYSIS.......................................................... 35 4.1 Introduction ............................................................................................................................35 4.2 Wing Control Specimen ........................................................................................................35 4.3 Planar Device 01 (PD-01) .....................................................................................................37 4.4 Planar Device 02 (PD-02) .....................................................................................................39 4.5 Non-Planar Device 01 (NPD-01) .........................................................................................41 4.6 Non-Pianar Device 02 (NPD-02) .........................................................................................43 4.7 Non-Pianar Device 03 (NPD-03) .........................................................................................47 4.8 Non Planar Device 04 (NPD-04) .........................................................................................49 4.9 Finai Candidates Discussion ................................................................................................52 4.9.1 Drag Coefficient versus Angie-of-Attack ...................................................................52 4.9.2 Lift Coefficient versus Angle-of-Attack ...................................................................... 53 IV 4.9.3 Lift-to-Drag Ratio versus Angle-of-Attack ................... 54 4.9.4 Lift Coefficient versus Drag Coefficient .....................................................................55 CHAPTER 5 WING-FUSELAGE JUNCTION SIMULATION ANALYSIS.....................................56 5.1 Introduction ............................................................................................................................. 56 5.2 Wing-Fuselage Junction Control Specimen ...................................................................... 56 5.3 Linear