THE ANALYSIS OF WING PERFORMANCE FOR RECONNAISSANCE UAV ZULKIFLI BIN YUSOF UNIVERSITI MALAYSIA PAHANG

THE ANALYSIS OF WING PERFORMANCE FOR RECONNAISSANCE UAV ZULKIFLI BIN YUSOF UNIVERSITI MALAYSIA PAHANG

The Analysis of Wing Performance for Reconnaissance UAV ZULKIFLI BIN YUSOF Report submitted in partial fulfillment of the requirements for the award of the degree of Bachelor of Mechanical Engineering Faculty of mechanical engineering UNIVERSITI MALAYSIA PAHANG NOVEMBER 2009

ii UNIVERSITI MALAYSIA PAHANG FACULTY OF MECHANICAL ENGINEERING We certify that the project entitled The Analysis of Wing Performance for Reconnaissance UAV is written by Zulkifli bin Yusof. We have examined the final copy of this project and in our opinion; it is fully adequate in terms of scope and quality for the award of the degree of Bachelor of Engineering. We herewith recommend that it be accepted in partial fulfilment of the requirements for the degree of Bachelor of Mechanical Engineering. Examiner Signature

iii SUPERVISOR S DECLARATION I hereby declare that I have checked this project and in my opinion this project is satisfactory in terms of scope and quality for the award of the degree Bachelor of Mechanical Engineering. Signature :.. Name of Supervisor : EN. AHMAD BASIRUL SUBHA BIN ALIAS Position : LECTURER Date :

iv STUDENT S DECLARATION I declared that this dissertation entitled The Analysis of Wing Performance for Reconnaissance UAV is the result of my own research except as cited in the references. The dissertation has not been accepted for any degree and is not currently submitted in candidature of any other degree. Signature :.. Name : ZULKIFLI BIN YUSOF ID Number : MA 06099 Date :

vi ACKNOWLEDGEMENTS First of all I am thankful to Allah SWT, the All Mighty, Who gave me the courage and strength to complete this work and fulfill the requirement of BMM 4924 Final Year Project subject. I hereby particularly grateful to my supervisor, Mr Ahmad Basirul Subha bin Alias, for giving me the moral support and encouragement as to complete this piece of work. He was always kind and cooperative. I am also indebted to Prof Dr. Rosli bin Abu Bakar, Dean of Mechanical Engineering Faculty and my fellow lecturers for giving such knowledge and experience to me since day one in Universiti Malaysia Pahang. They have been my source of inspiration and encouragement in this project. My special thanks go to fellow research cliques, Mohamed Zaid Bin Mohamed Zakaria and Izzan Hairi Bin Mohd Ibrahim whose help me during the designing process of this project, without them my research probably cannot finish in time. I also want to thanks others that help me with or without my knowledge to finish this work. In the end, I acknowledge the role of my family in the accomplishment of this work. The prayers of my parents and support from my brothers and sister has made all this possible to achieve. Thank you.

ix TABLE OF CONTENTS PANEL S DECLARATION SUPERVISOR S DECLARATION STUDENT S DECLARATION ACKNOWLEDGEMENTS ABSTRACT ABSTRAK TABLE OF CONTENTS LIST OF TABLES LIST OF FIGURES LIST OF ABBREVIATIONS LIST OF SYMBOLS LIST OF SUBSCRIPTS Page ii iii iv v vii viii ix xiii xiv xvi xvii xix CHAPTER 1 INTRODUCTION 1.1 Project Background 1 1.2 Project Objective 2 1.3 Project Scopes 2 1.4 Problem Statements 3 1.5 Project Assumptions 3 1.6 Technical Task Requirements 1.6.1 Introduction 1.6.2 Standard Requirement 1.6.3 Performance Parameters 1.6.4 Technical Level of Aircraft 1.6.5 Economical Parameters 1.6.6 Power Plant Requirement 1.6.7 Main System Parameter Requirements 1.6.8 Reliability and Maintainability 1.6.9 Unification Level 4 4 5 5 7 8 8 9 9 9

x 1.7 Mission Profile 10 CHAPTER 2 LITERATURE REVIEW 2.1 Introduction 11 2.2 History of Unmanned Aerial Vehicle (UAV) 12 2.3 Aircraft Design Textbooks and Researches 2.3.1 Morphing Wing HALE UAV 2.3.2 Design, Development and Manufacture of a Search and Rescue Unmanned Aerial Vehicle 2.3.3 Coastal Watch UAV 2.3.4 Roskam s Aircraft Design Series 2.3.5 Aircraft Performance and Design 2.4 Current UAV Types and Design 15 2.5 Wing Design and Configuration 17 2.6 Airfoil Shape 20 2.7 The UAV Powerplant 21 2.8 Camera for Reconnaissance 22 13 13 13 14 14 14 CHAPTER 3 RESEARCH METHODOLOGY 3.1 Introduction 23 3.2 Flow Chart 24 3.3 Conceptual Design 3.4 Software 3.3.1 Weight Estimation 3.3.2 Fuel Weight (W f ) Calculation 3.3.3 Aircraft Sizing 3.3.4 Drag Polar 3.3.5 FAR 23 Sizing 3.4.1 SolidWorks 3.4.2 XFLR5 3.4.3 DesignFoil 3.4.4 Profili 27 27 28 31 31 32 34 34 34 35 35

xi 3.5 Preliminary Sketches 35 CHAPTER 4 RESULTS AND DISCUSSIONS 4.1 Introduction 36 4.2 Matching Diagram 37 4.3 Airfoil Design Selection 4.3.1 Detailed Airfoil Requirement 4.3.2 NACA Airfoil Potential Candidates 4.3.3 Three Dimensional Effect 4.3.3 Two Dimensional Analysis 4.3.4 Airfoil Selection Process 4.4 Wing Profile Design 44 4.5 Mean Aerodynamic Chord Analysis 46 4.6 Three Dimensional Lift, C L max 49 4.7 Weight Distribution Analysis 49 4.8 Wing Simulation Analysis 51 4.9 CAD Design 4.9.1 Wing 3D Design 4.9.2 Full Body UAV 3D Design 4.10 Summarized Results 56 4.11 Discussions 57 38 38 39 39 40 42 52 53 54 CHAPTER 5 CONCLUSION AND RECOMMENDATIONS 5.1 Conclusions 61 5.2 Recommendations 62 REFERENCES 63 APPENDICES 65 A1 Gantt chart for FYP 1 65 A2 Gantt chart for FYP 2 66

xii A3 Flow Chart for Overall Project 67 B1 Engine Technical Data 68 B2 Camera Specification List 69 B3 Conceptual Design Calculation 70 B4 NACA Analysis Table 79 B5 NACA Plotted Data Analysis 81 B6 NACA Selected Profile 83 B7 NACA 6311 Analysis 85 B8 Mean Aerodynamic Chord Calculations 86 B9 Three Dimensional Lift Calculations 89 B10 Weight Distribution Calculations 90 B11 XFLR5 Wing Simulation Analysis 92 C1 Preliminary Sketches 94 C2 CAD Design (Wing) 97 C3 CAD Design (UAV Full body) 100

xiii LIST OF TABLES Table No. Page 2.1 Technical UAV data 16 2.2 Engine data 21 2.3 Camera technical data 22 3.1 Fuel Weight Division from Specified Mission Profile 29 3.2 Assumptions Properties 31 4.1 NACA Airfoil Analysis at Re = 1.0 x 10 5 39 4.2 NACA Airfoil Analysis at Re = 6.0 x 10 5 40 4.3 Weight balance to W TO 50 4.4 Summarized Results 56

xiv LIST OF FIGURES Figure No. Page 1.1 Mission Profile 10 2.1 Swept wing 17 2.2 Straight wing 17 2.3 Delta wing 18 2.4 Position of wing on aircraft 18 2.5 Wing notations 19 2.6 NACA nomenclature 20 2.7 Airfoil notation 20 2.8 RCV60-SP engine 21 2.9 FlyCamOne 2 camera 22 3.1 Flow chart for overall FYP 24 3.2 Technology Diagram 28 3.3 Graph W e, tent and W e, all Vs W TO 30 4.1 Matching Diagram 37 4.2 Graph C l Vs C d 41 4.3 Graph C l Vs Alpha and C d Vs Alpha 41 4.4 Graph C l /C d Vs Alpha and C m Vs Alpha 42 4.5 NACA 6311 profile 42 4.6 Graph C l Vs Alpha for NACA 6311 airfoil at 1.0 x 10 5 43 4.7 Graph C l Vs Alpha for NACA 6311 airfoil at 6.0 x 10 5 43 4.8 Effect of taper ratio on lift distribution 44

xv 4.9 Mid plane configuration 45 4.10 Parameter of half span wing 46 4.11 MAC for wing with λ = 0.5 48 4.12 Location of wing to the fuselage 48 4.13 XFLR5 simulation 51 4.14 Graph C L wing Vs Alpha 52 4.15 Half span wing profile 53 4.16 Wing profile top view 53 4.17 3D view of finish UAV model 54 4.18 Exploded view of UAV 55

xvi LIST OF ABBREVIATIONS 2D 3D AOA ARCAA CAD CFD FAR FPASS HALE MAC MAV NACA UAV USN Two Dimensional Three Dimensional Angle of Attack Australian Research Centre for Aerospace Automation Computer Aided Design Computational Fluid Dynamics Federal Air Regulation Force Protection Aerial Surveillance System High Altitude Long Endurance Mean Aerodynamic Chord Micro Air Vehicle National Advisory Committee for Aeronautics Unmanned Aerial Vehicle United States Navy WWI World War 1 WWII World War 2

xvii LIST OF SYMBOLS α η p Angle of attack Propeller efficiency π Product, or 3.142 ρ σ λ A Air density Air density ratio Tapered ratio Aspect ratio a, b Regression line constants defined by Equation 3.21, Roskam (2005) A, B Regression line constants defined by Equation 2.16, Roskam (2005) c, d Regression line constants defined by Equation 3.22, Roskam (2005) C C D C D o Chord length Drag coefficient Drag Polar CGR Climb gradient, defined by Equation 3.28, Roskam (2005) CGRP Climb gradient parameter, defined by Equation 3.30, Roskam (2005) C L C m D Lift coefficient Pitching moment coefficient Drag

xviii e E f FAR h Oswald s efficiency factor Endurance Equivalent parasite area Federal Air Regulation Altitude I p Power index, Equation 3.51, Roskam (2005) L L/D M ff P R RC Lift Lift-to-drag ratio Mission fuel fraction Power Range Rate of climb RCP Rate of climb parameter, Equation 3.24 and 3.25, Roskam (2005) Re s S S wet t V W Reynolds Number Distance, used in take-off and landing equations with subscripts Wing area Wetted area Time True airspeed weight

xix LIST OF SUBSCRIPTS cl cr E ff F h INS L ltr max OE PL PROP RC r s ST TO t tent Climb Cruise Empty Fuel fraction Mission fuel Altitude Vehicle instrumentation Landing Loiter Maximum Operating empty Payload Propulsion Rate of climb Root Stall Vehicle Structure Take-off Tip Tentative

xx tfo used w Trapped fuel and oil Used (fuel) Wing