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Novel Airframe Design for the Dual-Aircraft Atmospheric Platform Flight Concept

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Novel Airframe Design for the Dual-Aircraft Atmospheric Platform Flight Concept Dissertations and Theses 12-2012 Novel Airframe Design for the Dual-Aircraft Atmospheric Platform Flight Concept Eric Michael McKee Embry-Riddle Aeronautical University - Daytona Beach Follow this and additional works at: https://commons.erau.edu/edt Part of the Aerodynamics and Fluid Mechanics Commons, and the Mechanical Engineering Commons Scholarly Commons Citation McKee, Eric Michael, "Novel Airframe Design for the Dual-Aircraft Atmospheric Platform Flight Concept" (2012). Dissertations and Theses. 104. https://commons.erau.edu/edt/104 This Thesis - Open Access is brought to you for free and open access by Scholarly Commons. It has been accepted for inclusion in Dissertations and Theses by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. NOVEL AIRFRAME DESIGN FOR THE DUAL-AIRCRAFT ATMOSPHERIC PLATFORM FLIGHT CONCEPT by Eric Michael McKee A Thesis Submitted to the College of Engineering Department of Mechanical Engineering in Partial Fulfillment of the Requirements for the Degree of Master of Science in Mechanical Engineering Embry-Riddle Aeronautical University Daytona Beach, Florida December 2012 NOVEL AIRFRAME DESIGN FOR THE DUAL-AIRCRAFT ATMOSPHERIC PLATFORM FLIGHT CONCEPT by Eric Michael McKee This thesis was prepared under the direction of the candidate’s Thesis Committee Chair, Dr. William A. Engblom, Professor, Daytona Beach Campus, and Thesis Committee Members Snorri Gudmundsson, Professor, Daytona Beach Campus, and Glenn P. Greiner, Professor, Daytona Beach Campus, and has been approved by the Thesis Committee. It was submitted to the Department of Mechanical Engineering in partial fulfillment of the requirements for the degree of Master of Science in Mechanical Engineering Thesis Review Committee: ____________________________________ William A. Engblom, Ph.D. Committee Chair _________________________________ _______________________________ Snorri Gudmundsson, M.S. Glenn P. Greiner, M.S. Committee Member Committee Member ________________________________ _______________________________ Darris L. White, Ph.D. Charles F. Reinholtz, Ph.D. Graduate Program Chair, Department Chair, Mechanical Engineering Mechanical Engineering ________________________________ _______________________________ Maj Mirmirani, Ph.D. Robert Oxley, Ph.D. Dean, College of Engineering Associate Vice President of Academics ___________ Date ii Acknowledgements I would like to give thanks to our Lord and Savior, Jesus Christ, for giving me strength to pursue my dreams. I would like to thank Dr. William A. Engblom for the opportunity to work on this innovative and exciting research project as well as for his guidance and support throughout my work. Special thanks to Mr. Snorri Gudmundsson for his insightful knowledge and enthusiasm for aircraft design and his guidance throughout my studies and this research project. I would like thank Mr. Glenn Greiner for his advice throughout my studies and this research project. I would like thank all of my committee members for taking time out of their busy schedules to be part of my thesis review committee. My family has played an integral role during my studies and throughout my life. I would like to thank my parents, Mike and Laura, for their support and believing in me. I would like to thank my wonderful fiancée, Megan, for her unconditional love and support throughout the past year. iii Abstract Researcher: Eric Michael McKee Title: NOVEL AIRFRAME DESIGN FOR THE DUAL-AIRCRAFT ATMOSPHERIC PLATFORM FLIGHT CONCEPT Institution: Embry-Riddle Aeronautical University Degree: Master of Science in Mechanical Engineering Year: 2012 A high-altitude, long-endurance unmanned aerial airframe was designed for the innovative Dual-Aircraft Atmospheric Platform flight concept that exploits stratospheric wind velocity gradients to remain aloft indefinitely. Classical aircraft preliminary design techniques and high-fidelity tools were used to establish a baseline configuration. Performance characteristics of numerous airfoil profiles were evaluated with two- dimensional flow software in an effort to determine the best-candidate airfoil for the unique application. Vortex-Lattice method tools were used to investigate the sensitivity of three-dimensional design parameters upon overall vehicle aerodynamic performance and determine both static and dynamic stability characteristics of the airframe. Performance capabilities of the finalized airframe are demonstrated in a flight envelope diagram with applied gust loads per the Federal Aviation Regulations. The innovative tandem-wing design exhibits exceptional performance characteristics required for the flight concept. iv Table of Contents Thesis Review Committee .................................................................................................. ii Acknowledgements ............................................................................................................ iii Abstract .............................................................................................................................. iv List of Tables ..................................................................................................................... ix List of Figures ..................................................................................................................... x Nomenclature ................................................................................................................... xiii 1.0 Introduction ............................................................................................................. 1 1.1 Background ................................................................................................. 2 1.2 Dual-Aircraft Atmospheric Platform .......................................................... 4 1.3 Problem Statement ...................................................................................... 7 2.0 Design Methodology ............................................................................................... 8 2.1 Design Requirements .................................................................................. 8 2.1.1 Summary of Requirements ........................................................... 10 2.2 Numerical Simulation ............................................................................... 10 2.2.1 Vortex Lattice Method .................................................................. 10 2.2.2 VLM Limitations .......................................................................... 11 2.2.3 SURFACES .................................................................................. 11 2.2.3.1 Convergence Study ........................................................... 13 2.2.4 SURFACES Model ....................................................................... 14 2.3 Drag Analysis............................................................................................ 16 v 2.3.1 Pressure Drag ................................................................................ 17 2.3.2 Interference Drag .......................................................................... 19 2.3.3 Skin Friction Drag......................................................................... 19 2.3.4 Wave Drag .................................................................................... 21 2.3.5 Induced Drag ................................................................................. 21 3.0 Design Results ...................................................................................................... 23 3.1 Airfoil Selection ........................................................................................ 23 3.1.1 Airfoil Program Validation ........................................................... 23 3.1.2 Candidate Airfoils ......................................................................... 26 3.1.3 FX 63-137 Sub-Critical Airfoil ..................................................... 30 3.2 Airframe Configuration Selection............................................................. 34 3.2.1 Conventional ................................................................................. 34 3.2.2 Canard ........................................................................................... 36 3.2.3 Tandem-Wing ............................................................................... 38 3.2.4 Selected Airframe Configuration .................................................. 40 3.3 Wing Design ............................................................................................. 41 3.3.1 Wing Area ..................................................................................... 41 3.3.2 Aspect Ratio .................................................................................. 42 3.3.3 Taper Ratio.................................................................................... 46 3.3.4 Dihedral......................................................................................... 48 3.3.5 Incidence ....................................................................................... 49 3.4 Fuselage .................................................................................................... 50 3.5 Vertical Stabilizers .................................................................................... 51 vi 4.0 Airframe Aerodynamic Analysis .......................................................................... 53 4.1 Drag Results .............................................................................................
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