THE ANALYSIS OF WING PERFORMANCE FOR RECONNAISSANCE UAVumpir.ump.edu.my/17443/1/The analysis of wing perfor… ·  · 2017-04-10The Analysis of Wing Performance for Reconnaissance

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 engineeringUNIVERSITI 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 :

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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.

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TABLE OF CONTENTS

Page

PANEL’S DECLARATION ii

SUPERVISOR’S DECLARATION iii

STUDENT’S DECLARATION iv

ACKNOWLEDGEMENTS v

ABSTRACT vii

ABSTRAK viii

TABLE OF CONTENTS ix

LIST OF TABLES xiii

LIST OF FIGURES xiv

LIST OF ABBREVIATIONS xvi

LIST OF SYMBOLS xvii

LIST OF SUBSCRIPTS 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 Introduction1.6.2 Standard Requirement1.6.3 Performance Parameters1.6.4 Technical Level of Aircraft1.6.5 Economical Parameters1.6.6 Power Plant Requirement1.6.7 Main System Parameter Requirements1.6.8 Reliability and Maintainability1.6.9 Unification Level

4

455788999

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 UAV2.3.2 Design, Development and Manufacture of a Search and Rescue Unmanned Aerial Vehicle2.3.3 Coastal Watch UAV2.3.4 Roskam’s Aircraft Design Series2.3.5 Aircraft Performance and Design

13

1313

141414

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

CHAPTER 3 RESEARCH METHODOLOGY

3.1 Introduction 23

3.2 Flow Chart 24

3.3 Conceptual Design

3.3.1 Weight Estimation3.3.2 Fuel Weight (Wf) Calculation3.3.3 Aircraft Sizing3.3.4 Drag Polar3.3.5 FAR 23 Sizing

27

2728313132

3.4 Software

3.4.1 SolidWorks3.4.2 XFLR53.4.3 DesignFoil3.4.4 Profili

34

34343535

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 Requirement4.3.2 NACA Airfoil Potential Candidates4.3.3 Three Dimensional Effect4.3.3 Two Dimensional Analysis4.3.4 Airfoil Selection Process

38

3839394042

4.4 Wing Profile Design 44

4.5 Mean Aerodynamic Chord Analysis 46

4.6 Three Dimensional Lift, CL max 49

4.7 Weight Distribution Analysis 49

4.8 Wing Simulation Analysis 51

4.9 CAD Design

4.9.1 Wing 3D Design4.9.2 Full Body UAV 3D Design

52

5354

4.10 Summarized Results 56

4.11 Discussions 57

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 105 39

4.2 NACA Airfoil Analysis at Re = 6.0 x 105 40

4.3 Weight balance to WTO 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 We, tent and We, all Vs WTO 30

4.1 Matching Diagram 37

4.2 Graph Cl Vs Cd 41

4.3 Graph Cl Vs Alpha and Cd Vs Alpha 41

4.4 Graph Cl/Cd Vs Alpha and Cm Vs Alpha 42

4.5 NACA 6311 profile 42

4.6 Graph Cl Vs Alpha for NACA 6311 airfoil at 1.0 x 105 43

4.7 Graph Cl Vs Alpha for NACA 6311 airfoil at 6.0 x 105 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 CL 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 Two Dimensional

3D Three Dimensional

AOA Angle of Attack

ARCAA Australian Research Centre for Aerospace Automation

CAD Computer Aided Design

CFD Computational Fluid Dynamics

FAR Federal Air Regulation

FPASS Force Protection Aerial Surveillance System

HALE High Altitude Long Endurance

MAC Mean Aerodynamic Chord

MAV Micro Air Vehicle

NACA National Advisory Committee for Aeronautics

UAV Unmanned Aerial Vehicle

USN United States Navy

WWI World War 1

WWII World War 2

xvii

LIST OF SYMBOLS

α Angle of attack

ηp Propeller efficiency

π Product, or 3.142

ρ Air density

σ Air density ratio

λ Tapered ratio

A 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 Chord length

CD Drag coefficient

CD o Drag Polar

CGR Climb gradient, defined by Equation 3.28, Roskam (2005)

CGRP Climb gradient parameter, defined by Equation 3.30, Roskam (2005)

CL Lift coefficient

Cm Pitching moment coefficient

D Drag

xviii

e Oswald’s efficiency factor

E Endurance

f Equivalent parasite area

FAR Federal Air Regulation

h Altitude

Ip Power index, Equation 3.51, Roskam (2005)

L Lift

L/D Lift-to-drag ratio

Mff Mission fuel fraction

P Power

R Range

RC Rate of climb

RCP Rate of climb parameter, Equation 3.24 and 3.25, Roskam (2005)

Re Reynolds Number

s Distance, used in take-off and landing equations with subscripts

S Wing area

Swet Wetted area

t Time

V True airspeed

W weight

xix

LIST OF SUBSCRIPTS

cl Climb

cr Cruise

E Empty

ff Fuel fraction

F Mission fuel

h Altitude

INS Vehicle instrumentation

L Landing

ltr Loiter

max Maximum

OE Operating empty

PL Payload

PROP Propulsion

RC Rate of climb

r Root

s Stall

ST Vehicle Structure

TO Take-off

t Tip

tent Tentative

xx

tfo Trapped fuel and oil

used Used (fuel)

w Wing