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UNIVERSITI PUTRA MALAYSIA
CATUR SETYAWAN KUSUMOHADI
FK 2011 148
LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF WAU BULAN WING-TAIL CONFIGURATION WITH
SELECTED AIRFOIL PROFILE
LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF WAU BULAN
WING-TAIL CONFIGURATION WITH SELECTED AIRFOIL PROFILE
By
CATUR SETYAWAN KUSUMOHADI
Thesis Submitted to the School of Graduate Studies, Universiti Putra Malaysia,
in Partial Fulfilment of the Requirement for the Degree of Doctor of Philosophy
September 2011
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DEDICATION
This Thesis is Dedicated to my:
My Parents
Bapak & Ibu Soekemi
Ibu Wasithoh Bahran
My wife
Siti Zakiyah
My child
Ibnu Afif Kusumahadi
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Abstract of thesis presented to the Senate of Universiti Putra Malaysia in fulfillment
of the requirement for the degree of Doctor of Philosophy
LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF WAU BULAN
WING-TAIL CONFIGURATION WITH SELECTED AIRFOIL PROFILE
by
CATUR SETYAWAN KUSUMOHADI
September 2011
Chairman : Prof. Ir. Shah Nor Basri, PhD
Faculty : Faculty of Engineering
Wau bulan is one of the traditional Malaysia kites. Wau bulan consists of two parts
which are wing and tail. Its configuration shows possible application as baseline
planform of an aircraft. Wau bulan wing tail configuration is indicated as
controllable and could meet the stability requirements. It is implied that wau bulan
can be used as “Sensorcraft UAV configuration” that can meet the requirement of
360o unobstructed radar vision area. In this research, this wau bulan planform will be
used as baseline of mini UAV configuration.
Wau bulan wing planform shape that is close to elliptical shape, theoretically will
have high efficiency factor. However, wau bulan has a low aspect ratio wing that
causes high induced drag and will generate a low lift over drag ratio. Furthermore,
wau bulan large tail area and short tail boom can also create significant trim drag.
The focus of the research is to investigate the longitudinal aerodynamic
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characteristics of wau bulan wing tail configuration. It aims to verify that the wau
bulan can fulfill the requirements of surveillance mini UAV.
The research consists of baseline geometry definition, computational analysis and
wind tunnel testing of isolated wau bulan wing and wing-tail configuration. Results
of analysis would be compared with the assumed ones from initial sizing process.
The baseline geometry was determined based on the initial sizing results, whereby
initial sizing is the standard procedure of UAV initial calculation to predict the
weight, power loading and wing loading based on surveillance mini UAV
performance criteria. Airfoil was applied to create thickness of baseline geometry
planform, where Kennedy Marsden Mod airfoil was chosen. It is a thick airfoil and
was designed for low Reynolds number flow.
FLUENT software was used as a tool for computational analysis, since it can
accommodate 2D and 3D models. The results show the correlation of longitudinal
aerodynamic characteristics between 2D airfoil with and without boundary layer
mesh, isolated wing and wing tail configuration. The gaps between calculation
results were justified by using the validation process. The boundary layer mesh
shows significant effect toward aerodynamics calculation.
Wind tunnel testing was conducted at UPM low speed open wind tunnel. This
suction type wind tunnel is equipped with external balance to measure the
aerodynamic forces and moments. Wind tunnel results show similar value of
aerodynamics coefficient especially lift coefficient, between isolated wing and wing
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tail configuration. The effect of symmetrical tail cross section was observed at high
angle of attack when the tail produces lift.
Despite gaps between the experimental and computational results, the values still can
be used to predict longitudinal aerodynamic characteristics of wau bulan wing tail
configuration through validation process. The results show that the maximum lift
coefficient of wing-tail configuration is close to the 2D airfoil one. Based on this
condition, the improvement of wau bulan UAV can be predicted by using the 2D
airfoil data.
The analysis results prove that the longitudinal aerodynamic parameters of wau bulan
UAV can be achieved. The maximum lift coefficient and lift over drag ratio values
from computational and wind tunnel test are higher than the assumed ones during
performance sizing. These results give opportunities to improve wau bulan UAV
performance because the excess value could compensate additional weight or fuel.
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Abstrak thesis yang dikemukakan kepada Senat Universiti Putra Malaysia sebagai
memenuhi keperluan untuk ijazah Doktor Falsafah
CIRI-CIRI AERODINAMIK PADA ARAH LONGITUDINAL UNTUK
TATARAJAH SAYAP-EKOR DARI PADA WAU BULAN UAV DENGAN
MENGGUNAKAN PROFAIL AIRFOIL YANG TERPILIH
oleh
CATUR SETYAWAN KUSUMOHADI
September 2011
Pengerusi : Prof. Ir. Shah Nor Basri, PhD
Faculti : Fakulti Kejuruteraan
Wau bulan ialah salah satu layang-layang tradisional Malaysia. Layang-layang Wau
bulan terdiri daripada dua bahagian ianya bahagian sayap dan ekor. Konfigurasi ini
juga menunjukkan kemungkinan untuk diguna pakai sebagai planform asas pesawat.
Konfigurasi ekor sayap mengesahkan bahawa konfigurasi ini boleh dikawal dan
dapat memenuhi keperluan kestabilan. Konfigurasi ini juga membuktikan bahawa
wau bulan boleh digunakan sebagai konfigurasi daripada “Sensorcraft UAV " yang
boleh memenuhi penglihatan radar pada kawasan 360o yang tanpa halangan. Dalam
kajian ini, planform wau bulan akan digunakan sebagai asas konfigurasi UAV mini.
Secara teorinya, bentuk planform daripada sayap wau bulan adalah berhampiran
dengan bentuk elips yang mempunyai satu faktor efisiensi yang cukup tinggi. Walau
bagaimanapun, wau bulan mempunyai aspek rasio sayap yang rendah ianya akan
menyebabkan daya heret tinggi dan akan mengkurangkan nilai nisbah daya angkat
terhadap daya heret. Tambahan pula, ekor wau bulan yang besar dan paip sambungan
ekor yang pendek juga boleh mewujudkan tambahan daya heret trim yang ketara.
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Tumpuan penyelidikan ialah untuk menyiasat ciri-ciri aerodinamik ekor konfigurasi
sayap wau bulan pada arah longitudinal. Matlamat ini dinyatakan untuk dapat
mengesahkan bahawa wau bulan dapat memenuhi persyaratan sebagai mini UAV
untuk pengawasan.
Penyelidikan mengandungi takrif geometri asas, analisis komputasi dan ujian
terowong angin daripada sayap dan konfigurasi sayap-ekor wau bulan. Kumpulan
daripada keputusan analisis akan dibandingkan nilai yang dianggarkan pad proses
penentuan saiz awal.
Geometri garis asas dasar tersebut ditentukan berasaskan kepada hasil proses
penentuan saiz awal. Penentuan saiz awal ialah prosedur standard daripada pengiraan
awal untuk suatu UAV ianya meramalkan berat, loading kuasa dan bebanan sayap
yang berdasarkan kepada kriteria prestasi daripada surveillance mini UAV. Aerofoil
untuk sayap dipilih semasa takrif geometri asas dilakukan. Airfoil Kennedy Marsden
Mod telah dipilih. Ia adalah airfoil yang tebal dan direka bentuk untuk aliran dengan
nombor Reynolds yang rendah.
Perisian FLUENT telah diguna sebagai alat bagi analisis komputasi. Perisian ini
boleh diguna untuk pengiraan model 2D dan 3D. Keputusan analisis komputasi
menunjukkan hubung kait daripada ciri-ciri aerodinamik pada arah longitudinal
aerofoil 2D dengan dan tanpa grid boundary layer, sayap dan konfigurasi ekor sayap.
Boundary layer mempunyai kesan yang besar ke atas pengiraan aerodinamik.
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Ujian terowong angin telah dijalankan di terowong angin terbuka berkelajuan rendah
yang berada dekat UPM. Terowong angin jenis sedutan ini dilengkapi dengan
external balance untuk mengukur daya dan momen aerodinamik. Keputusan
terowong angin menunjukkan bahawa sayap dan konfigurasi ekor sayap mempunyai
nilai aerodinamik yang sama terutamanya nilai daya angkat maksima. Kesan
daripada ekor simetri ditunjukkan pada sudut serang yang tinggi apabila ekor
menghasilkan daya angkat.
Walaupun terdapat perbezaan antara keputusan uji kaji dan komputasi, tetapi dengan
menggunakan proses pengesahan, nilai-nilai yang sedia ada boleh diguna untuk
meramal ciri-ciri aerodinamik konfigurasi sayap-ekor wau bulan pada arah
longitudinal. Keputusan yand diperolehi menunjukkan bahawa daya angkat
maksimum konfigurasi sayap-ekor berhampiran dengan daya angkat maksima
daripada airfoil 2D. Berdasarkan kenyataan ini, peningkatan prestasi daripada wau
bulan UAV boleh diramalkan dengan menggunakan data airfoil 2D.
Keputusan analisis membuktikan bahawa parameter aerodinamik daripada wau bulan
UAV pada arah longitudinal boleh dicapai. daya angkat maksimum dan nisbah daya
angkat ke atas daya heret daripada proses analisis ialah lebih tinggi daripada yang
dianggarkansemasa penentuan saiz awal. Keputusan ini memberikan peluang-
peluang untuk peningkatan wau bulan UAV kerana ini nilai yang berlebih ini boleh
diguna untuk memberikan tambahan berat atau minyak.
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ACKNOWLEDGEMENTS
I would like to express my sincere most appreciation and deepest gratitude to
Professor Ir. Dr. Shah Nor Basri who has been my chairman of supervisory
committee. Since then, he has given me his wise counsel, guidance and valuable help
whenever I needed. I am ever grateful to his unflagging guidance, support and
encouragement.
I would also like to thank Dr. Ir. Prasetyo Edi who was my first chairman of
supervisory committee. He was who initially invited me to take the PhD program in
the Department of Aerospace, UPM.
I would like to thank my supervisory committee members, Associate Professor
Mohd. Ramly Ajir and Dr. Abdul Aziz Jaafar for their valuable guidance, comments
and suggestions, which were very helpful throughout my research work.
I also want to express my grateful to Dr-Ing. Surjatin Wiriadidjaja who gave me his
wise counsel, guidance and encouragement.
I am particularly grateful to my friend Dr. Azmin Shakrine for his active help and
encouragement during this study. I want to thank Mr. Ropie Mat for his assistance,
encourage and accompany during hard time in this study.
I like to thank my examination committee, Assoc. Prof. Dr. Renuganth A/L
Varatharajoo, Prof. Dr. Harijono Djojodihardjo, Assoc. Prof. Dr-Ing. Surjatin
Wiriadidjaja, and Prof Fei-Bin Hsiao for their corrections and recommendation of the
thesis.
I would like to thank all of the staff members in the Department of Aerospace
Engineering, UPM for their direct and indirect help and co-operation throughout the
period of my study.
Finally, I like to thank all of my friends in the Indonesia Students Association (PPI)
in UPM for their support and assistance during my stay in Malaysia.
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I certify that a Thesis Examination Committee has met on 22 September 2011 to
conduct the final examination of Catur Setyawan Kusumohadi on his thesis entitled
“Longitudinal Aerodynamic Characteristics of Wau Bulan Wing-Tail Configuration
with Selected Airfoil Profile” in accordance with the Universities and University
Collegeg Act 1971 and the Constitution of the Universiti Putra Malaysia [P.U.(A)
106] 15 March 1998. The Committee recommends that the student be awarded the
Doctor of Philosophy.
Members of the Thesis Examination Committee were as follows:
Renuganth A/LVaratharajoo, PhD
Associate Professor
Faculty of Engineering
University Putra Malaysia
(Chairman)
Harijono Djojodihardjo, PhD
Professor
Faculty of Engineering
University Putra Malaysia
(Internal Examiner)
Surjatin Wiriadidjaja, PhD
Associate Professor
Faculty of Engineering
University Putra Malaysia
(Internal Examiner)
Fei-Bin Hsiao, PhD
Professor
National Cheng Kung University
Taiwan
(External Examiner)
SEOW HENG FONG, PhD
Professor and Deputy Dean
School of Graduate Studies
Universiti Putra Malaysia
Date: 22 September 2011
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OPYRIGHT U
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xi
This thesis was submitted to the Senate of Universiti Putra Malaysia and has been
accepted as fulfillment of the requirement for the degree of Doctor of Philosophy.
The members of the Supervisory Committee were as follows:
Shah Nor Basri, PhD
Professor
Faculty of Engineering
University Putra Malaysia
(Chairman)
Mohd Ramly Ajir
Associate Professor
Faculty of Engineering
University Putra Malaysia
(Member)
Abdul Aziz Jaafar, PhD
Senior Lecturer
Faculty of Engineering
University Putra Malaysia
(Member)
BUJANG BIN KIM HUAT, PhD
Professor and Dean
School of Graduate Studies
Universiti Putra Malaysia
Date:
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DECLARATION
I declare that the thesis is my original work except for quotations and citations,
which have been duly acknowledged. I also declare that it has not been previously,
and is not concurrently, submitted for any other degree at Universiti Putra Malaysia
or at any other institution.
CATUR SETYAWAN KUSUMOHADI
Date: 22 September 2011
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TABLE OF CONTENTS
Page
DEDICATION ii
ABSTRACT iii
ABSTRAK vi
ACKNOWLEDGEMENTS ix
APPROVAL x
DECLARATION xii
TABLE OF CONTENTS xiii
LIST OF TABLES xvii
LIST OF FIGURES xix
LIST OF ABBREVIATIONS xxxii
CHAPTER
1 INTRODUCTION 1
1.1 Background 1
1.2 Problem Statement 2
1.3 Research Aim and Objectives 4
1.4 Scope of the Thesis 4
1.5 Significance of the Thesis 5
1.6 Outline of the Thesis 6
2 LITERATURE REVIEW 8
2.1 “Wau” - Malaysia’s Kites 8
2.2 Wau bulan Planform 9
2.2.1 Aerodynamic Characteristics 10
2.2.2 Structure 12
2.2.3 Stability and Control 13
2.2.4 Sensor placement 13
2.3 Wing Configurations 13
2.3.1 Wing Planform 15
2.3.2 Wing Vertical Location 17
2.4 Researches on Wing Configuration Concepts 18
2.4.1 Low Aspect Ratio Wing 18
2.4.2 Non Planar Wing 19
2.4.3 Crescent Shaped Wing 19
2.4.4 Blended Wing-Body 20
2.5 Empennage/Tail configurations 21
2.6 Previous Research on Wing-Tail Configuration Concepts 22
2.6.1 Joined/Box wing 22
2.6.2 Ring/Circular wing 23
2.7 Closure 24
3 METHODOLOGY 26
3.1 Baseline Geometry Definition 26
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3.2 Computational Aerodynamics Analysis 27
3.2.1 Flow condition for CFD Analysis 29
3.2.2 2D Airfoil Analysis Plan 29
3.2.3 3D Wau bulan Wing Analysis Plan 30
3.2.4 Wing-Tail Configuration Analysis Plan 32
3.3 Wind Tunnel Testing 32
3.3.1 Wind Tunnel Flow Quality 34
3.3.2 Model Preparation and Installation 35
3.3.3 Models Testing Process 35
4 BASELINE GEOMETRY DEFINITION 41
4.1 Flow condition 41
4.2 Baseline Wing Airfoil 43
4.2.1 Low Reynolds Number Airfoil 43
4.2.2 Thick airfoil 43
4.2.3 High CL/CD 44
4.3 Chosen Airfoil Aerodynamic Characteristics 44
4.4 Baseline Planform 45
5 RESULTS AND DISCUSSION OF COMPUTATIONAL ANALYSIS 48
5.1 Model Geometry and Meshing 48
5.1.1 Boundary and Mesh Optimization 48
5.1.2 2D Airfoil 48
5.1.3 3D Isolated Wau bulan Wing 52
5.1.4 Wing-Tail Configuration 55
5.1.5 Mesh Size Determination 56
5.2 Validation of FLUENT Software 57
5.2.1 2D Airfoil Model Validation 58
5.2.2 3D Model Validation 61
5.2.3 Comparison between 2D Model and 3D Model 64
5.3 Results 65
5.3.1 2D Airfoil 65
5.3.1.1 Contour Plot 65
5.3.1.2 Aerodynamics Coefficients 68
5.3.1.3 Boundary Layer Mesh Effects 71
5.3.1.4 Turbulence Models Effects 72
5.3.1.5 Airfoil Types Effect 73
5.3.2 Wing Configuration 76
5.3.2.1 Aerodynamics Coefficients 76
5.3.2.2 Wing Models Comparison 79
5.3.3 Wing-Tail Configuration 82
6 MODEL PREPARATION AND WIND TUNNEL TESTS RESULTS AND
DISSCUSSION 86
6.1 Wind Tunnel’s Airflow Conditions 86
6.1.1 Airflow Reynolds Number during Testing 87
6.1.2 Airflow Velocity Correction 88
6.2 Model Preparation 89
6.2.1 Model Geometry 89
6.2.2 Wind Tunnel Model Production 89
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6.2.3 Correction Factor due to the Model Defects 91
6.3 Model Installation 92
6.3.1 Isolated Wing Model 92
6.3.2 Wing Tail Configuration Model 94
6.3.3 Installation Correction Factors 94
6.4 Wind Tunnel Test Results and Discussion 96
6.4.1 Isolated Wing 96
6.4.2 Wing-Tail Configuration 100
6.4.3 Comparison between Isolated Wing and Wing-Tail Configuration 103
7 RESULTS Comparison 106
7.1 Comparison of Computational and Experimental Results 106
7.2 Comparison of Aerodynamics Analysis Results and Assumed Aerodynamic
Characteristics of Designed Wau Bulan UAV 110
8 CONCLUSION AND RECOMMENDATIONS 112
8.1 Summary 112
8.2 Conclusion 113
8.3 Recommendation for future work 114
REFERENCES 115
Appendix A: UAV Initial Sizing 123
A.1 UAV Conceptual Design Method 123
A.2 Design Concepts 125
A.3 Mission Requirements 125
A.4 Performance Requirements 126
A.4.1 Cruise 126
A.4.2 Loiter 127
A.4.3 Mission Profile 127
A.5 Competitors Data Analysis 127
A.6 Initial weight sizing 129
A.6.1 Input Parameter 130
A.6.2 Aerodynamic Coefficients Assumptions 130
A.6.3 Propulsion Data Assumptions 130
A.6.4 Results 130
A.7 Performance Sizing 131
A.7.1 Stall Speed 131
A.7.2 Take Off 131
A.7.3 Landing 131
A.7.4 Cruise 132
A.7.5 Climb 132
A.7.6 Results 132
Appendix B: Airfoil Selection 134
B.1 Low Speed Airfoil Properties 134
B.2 Chosen Airfoil Specification 136
B.2.1 Eppler E397 (human powered aircraft airfoil) 136
B.2.2 NLF 1015 (natural laminar flow airfoil) 136
B.2.3 Wortmann FX 63-137 (human power aircraft airfoil) 137
B.2.4 KM Mod (high lift airfoil modified from Kennedy Marsden
Airfoil) 138
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Appendix C: FLUENT Parameters 140
C.1 Pressure Far-Field Boundary Type 140
C.2 Flow Modeling in FLUENT 141
C.2.1 Laminar Modeling 141
C.2.2 Laminar-Turbulence Transition 142
C.2.3 Turbulence Modeling 143
Appendix D: Airfoil Model Computational Results 147
D.1 Mesh Effect on Eppler E397 Airfoil 147
D.2 Effect of viscous modeling E397 airfoil 151
D.3 Mesh Effect on Wortmann FX 63-137 airfoil 155
D.4 Mesh Effect on KM Mod airfoil 165
D.5 Effect of viscous modeling KM Mod airfoil 171
D.6 Mesh Effect on NLF 1015 airfoil 175
D.7 Effect of viscous modeling NLF 1015 airfoil 179
Appendix E: Isolated Wing Computational Results 183
E.1 Effects of Mesh Size 183
E.2 Effects of Viscous Modeling 192
BIODATA OF STUDENT 203
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