THE ANALYSIS OF WING PERFORMANCE FOR RECONNAISSANCE UAV ZULKIFLI BIN YUSOF UNIVERSITI MALAYSIA PAHANG
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1 THE ANALYSIS OF WING PERFORMANCE FOR RECONNAISSANCE UAV ZULKIFLI BIN YUSOF UNIVERSITI MALAYSIA PAHANG
2 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
3 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
4 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 :
5 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 Date :
6 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.
7 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 Project Objective Project Scopes Problem Statements Project Assumptions Technical Task Requirements Introduction Standard Requirement Performance Parameters Technical Level of Aircraft Economical Parameters Power Plant Requirement Main System Parameter Requirements Reliability and Maintainability Unification Level
8 x 1.7 Mission Profile 10 CHAPTER 2 LITERATURE REVIEW 2.1 Introduction History of Unmanned Aerial Vehicle (UAV) Aircraft Design Textbooks and Researches Morphing Wing HALE UAV Design, Development and Manufacture of a Search and Rescue Unmanned Aerial Vehicle Coastal Watch UAV Roskam s Aircraft Design Series Aircraft Performance and Design 2.4 Current UAV Types and Design Wing Design and Configuration Airfoil Shape The UAV Powerplant Camera for Reconnaissance CHAPTER 3 RESEARCH METHODOLOGY 3.1 Introduction Flow Chart Conceptual Design 3.4 Software Weight Estimation Fuel Weight (W f ) Calculation Aircraft Sizing Drag Polar FAR 23 Sizing SolidWorks XFLR DesignFoil Profili
9 xi 3.5 Preliminary Sketches 35 CHAPTER 4 RESULTS AND DISCUSSIONS 4.1 Introduction Matching Diagram Airfoil Design Selection Detailed Airfoil Requirement NACA Airfoil Potential Candidates Three Dimensional Effect Two Dimensional Analysis Airfoil Selection Process 4.4 Wing Profile Design Mean Aerodynamic Chord Analysis Three Dimensional Lift, C L max Weight Distribution Analysis Wing Simulation Analysis CAD Design Wing 3D Design Full Body UAV 3D Design 4.10 Summarized Results Discussions CHAPTER 5 CONCLUSION AND RECOMMENDATIONS 5.1 Conclusions Recommendations 62 REFERENCES 63 APPENDICES 65 A1 Gantt chart for FYP 1 65 A2 Gantt chart for FYP 2 66
10 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
11 xiii LIST OF TABLES Table No. Page 2.1 Technical UAV data Engine data Camera technical data Fuel Weight Division from Specified Mission Profile Assumptions Properties NACA Airfoil Analysis at Re = 1.0 x NACA Airfoil Analysis at Re = 6.0 x Weight balance to W TO Summarized Results 56
12 xiv LIST OF FIGURES Figure No. Page 1.1 Mission Profile Swept wing Straight wing Delta wing Position of wing on aircraft Wing notations NACA nomenclature Airfoil notation RCV60-SP engine FlyCamOne 2 camera Flow chart for overall FYP Technology Diagram Graph W e, tent and W e, all Vs W TO Matching Diagram Graph C l Vs C d Graph C l Vs Alpha and C d Vs Alpha Graph C l /C d Vs Alpha and C m Vs Alpha NACA 6311 profile Graph C l Vs Alpha for NACA 6311 airfoil at 1.0 x Graph C l Vs Alpha for NACA 6311 airfoil at 6.0 x Effect of taper ratio on lift distribution 44
13 xv 4.9 Mid plane configuration Parameter of half span wing MAC for wing with λ = Location of wing to the fuselage XFLR5 simulation Graph C L wing Vs Alpha Half span wing profile Wing profile top view D view of finish UAV model Exploded view of UAV 55
14 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
15 xvii LIST OF SYMBOLS α η p Angle of attack Propeller efficiency π Product, or 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
16 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
17 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
18 xx tfo used w Trapped fuel and oil Used (fuel) Wing
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