The 4 AUN/SEED-Net Regional Conference in

The 4th AUN/SEED-Net
Regional Conference in Mechanical
and Aerospace Technology
“Changing Tomorrow’s Life by Development Today’s
Technologies”
Oscar Saigon Hotel, January 10-11, 2012
ISBN: 978-604-73-0701-2
Ho Chi Minh City University of Technology
Ho Chi Minh City, Vietnam
Conference Organizer
• JICA AUN/SEED-Net
• Faculty of Transportation Engineering, Ho Chi Minh City University of
Technology
• Faculty of Mechanical Engineering, Ho Chi Minh City University of
Technology
• Faculty of Mechanical and Aerospace Engineering, Institute Technology
Bandung
• Support from Hanoi University of Science and Technology.
Organizing Committee
• Conference General Chairman
• Conference General Co-Chairman
• Conference Organizing Chairs
• Conference Organizing Co-Chairs
• Local scientific committee
• Conference Secretariat
• Publication and Proceedings
• International Advisor Board
Dr. Nguyen Le Duy Khai
Assoc.Prof.Dr. Tran Thien Phuc
Dr. Nguyen Ngoc Dung
Assoc.Prof.Dr. Andi Isra Mahyuddin
Assco.Prof.Dr. Tran Thien Phuc
Assoc.Prof.Dr. Pham Xuan Mai
Assoc.Prof. Dr. Nguyen Tan Tien
Assoc.Prof. Nguyen Thach
Assof.Dr. Nguyen Anh Thi
Dr. Le Dinh Tuan
Dr. Tran Huu Nhan
Dr. Nguyen Ngoc Dung
Dr. Phan Anh Tuan
Dr. Le Xuan Truong
Dr. Huynh Thanh Cong
Prof. Dr. OBI Shinnosuke
Prof. Dr. SUZUKI Shinji
Assoc. Prof. Dr. Andi Isra Mahyuddin
Assoc. Prof. Dr. Iman K. Reksowardojo
Assoc. Prof. Dr. Kanit Wattanavichien
Prof. Dr. Archie Maglaya
Assoc. Prof. Dr. Le Anh Tuan
Assoc.Prof.Dr. Tran Thanh Hai Tung
Proceeding of
The 4th AUN/SEED-Net Regional Conference
in Mechanical and Aerospace Technology
“Changing Tomorrow’s Life by Development Today’s Technologies”
Editor
Dr. Nguyen Ngoc Dung
ISBN: 978-604-73-0701-2
The Publisher and the Editor of its publication assume no
responsibility for the statements or opinions expressed in
papers or presentations by the contributors to this
conference.
Ho Chi Minh City, Vietnam.
WELCOME ADDRESS
RECTOR OF HCMUT
I am pleased, on behalf of Ho Chi Minh City University of Technology, to welcome all
the distinguished guests to participate in the 4th AUN/SEED-Net Regional Conference
in Mechanical and Aerospace Technology in Vietnam, from 10-12 January, 2012. We
are indeed honored to have you here with us.
Following the success of previous conferences, this year Ho Chi Minh City University
of Technology is proud to be appointed the lead organizer and hosted for this event.
And here we are now at Ho Chi Minh City to continue annual conference series. We
are glad that we will have opportunities in this conference and after it to learn from our
colleagues from many countries in the world.
I would like to take the opportunity to extend the gratitude and thanks to all the role
players that have made the conference possible. Thank the Local Organizing
Committee for their hard work and effort in planning and coordinating this event. Other
organizations that have contributed to this event include JICA AUN/SEED-Net, Faculty
of Mechanical and Aerospace Engineering, Institute Technology Bandung, Hanoi
University of Science and Technology.
With a large number of participants, making our conference a truly international one,
we are sure that this conference will be a memorable event. We hope that this
conference will help you better understand new and emerging technologies in the
various areas of mechanical and aerospace engineering.
We truly value your participation and support for this conference. Thank you so much
for coming and for your attention. Hope that this conference will bring the best to all
participants.
Prof. Vu Dinh Thanh
Rector, Ho Chi Minh City University of Technology
WELCOME ADDRESS
CONFERENCE GENERAL CHAIR
On behalf of the organizing committee, I would like to invite you to participate in the 4th
AUN/SEED-Net Regional Conference, Vietnam 2012 which will be held between
January 10-11, 2012 at Oscar Saigon Hotel, Ho Chi Minh City, Vietnam.
Regional Conference in Mechanical and Aerospace Technology is an annual
conference series. This conference serves as a platform for presenting new and
emerging technologies in the various areas of mechanical and aerospace engineering
and how such technologies are utilized in the industry and appropriated to the
community to create high socio – economic impact. The regional conference is also a
venue to discuss the most updated technology and the research of regional issues and
public interests in order to contribute to the community and to draw support from the
industrial and the governmental sectors.
The conference is organized by Ho Chi Minh City University of Technology,
AUN/SEED-net, Institute Technology Bandung and Hanoi University of Science and
Technology to present your exciting and novel findings, and to hear about the most
recent and important advances in mechanical and aerospace technology. We wish to
share experiences and contribution towards building the framework for sustainable
development in the 21st century.
Here, please allow me to express my sincere welcome on behalf of the Organizing
Committee to all the experts and friends form abroad and within Vietnam that have
participated in the conference! Thank you very much for attending this conference in
spite of your busy schedules. We are very grateful to you, and to all of our guest
speakers, for coming all the way here.
Assoc.Prof. Dr. Nguyen Huu Huong
Dean, Faculty of Transportation Engineering
Conference General Chairman
TIME TABLE
Day 1 (Tuesday, 10 January 2012)
Time
Saigon-Hanoi room
08:00 - 08:30
Registration
08:30 - 09:00
Opening
09:00 - 10:45
Plenary Session
10:45 - 11:00
11:00 - 12:20
12:20 - 13:30
13:30 - 15:10
Topic: Flight Physics
17:00 - 18:00
Coffee Break
Topic: Mechanical
systems
Board room
Topic: Energy Systems
Lunch (Starlight Restaurant, 11th floor)
Topic: Mechanical
Topic: Flight Physics
systems
Topic: Energy Systems
15:10 - 15:30
15:30 - 16:50
Sixty-Eight Hall
Topic: Flight Physics
Coffee Break
Topic: Mechanical
systems
Topic: Energy Systems
Discussion on future collaboration by AUN/SEED-Net staff
(Saigon-Hanoi room)
Day 2 (Wednesday, 11 January 2012)
Time
08:00 - 08:30
08:30 - 10:10
Activities
Registration
Topic: Flight Physics
10:10 - 10:30
10:30 - 12:10
14:50 - 15:10
15:10 - 16:30
Topic: Thermal Engineering
Coffee Break
Topic: Structure and
Materials
12:10 - 13:10
13:10 - 14:50
Topic: Mechanical
systems
Topic: Fluid Dynamic
Topic: Thermal Engineering
Lunch (Starlight Restaurant, 11th floor)
Topic: Structure and
Materials
Topic: Fluid Dynamic
Coffee Break
Closing ceremony
Topic: Others
PRESENTATION SCHEDULE
Day 1 (Tuesday, 10 January 2012)
Room
Time
Saigon - Hanoi Room
Presentati
on Number
11:00 - 12:20
11:00 - 11:20
Topic: Flight Physics
FP-01
Evaluation of Airfoils that Suitable for a Forward Swept Wing
Amalia Ema
Flight Physics Research Group – Aeronautics and Astronautics Study
Program, Faculty of Mechanical and Aerospace Engineering, Indonesia.
11:20 - 11:40
11:40 - 12:00
FP-02
FP-03
Numerical Simulation of Vortical Flow on High Attack Angle of Delta
Wing using RANS
M. Nurrachman, Romie O. Bura and Albert Meigo R.E.Y
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia.
High Angle-of-Attack Flight Dynamics Analysis Using Bifurcation
and Continuation Approach
Hendarko
Faculty of Mechanical and Aerospace Engineering
Institut Teknologi Bandung, Indonesia.
12:00 - 12:20
FP-04
Estimation of Aerodynamic Parameter of Micro Aerial Vehicle Using
Total Least Squares
Muhammad H., Thien H. P. and Mulyanto T.
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia.
12:20 - 13:30
Lunch (Starlight Restaurant, 11th floor)
13:30 - 15:10
13:30 - 13:50
Topic: Flight Physics
FP-05
Pseudo shock wave in the case suddent inserts the trust into
suppersonic flow on rectangular ducts
Hung Nguyen Phu, Nakashima Naoki and Umemura Akia
Deptement of Aeronautical and Space Engineering, Hanoi university of
Science and Technology, Hanoi, Vietnam.
13:50 - 14:10
FP-06
Development of a Wind Tunnel Test Equipment for 3 DoF Aeroelastic
Experimental Studies
R.A. Sasongko, M. Akbar, F.S. Pranoto, Pramudita S. P.
Department of Aeronautics and Astronautics, Faculty of Mechanical and
Aerospace Engineering, Institut Teknologi Bandung, Indonesia.
14:10 - 14:30
14:30 - 14:50
14:50 - 15:10
FP-07
FP-08
FP-09
Drag Minimization of Low Reynolds Number Airfoil Using Single
Objective Particle Swarm Optimization
Pramudita S. Palar, Lavi R.Zuhal
Flight Physics Research Group, Faculty of Mechanical and Aerospace
Engineering, Institut Teknologi Bandung, Indonesia.
Modeling and Identification of Longitudinal Dynamic Model of Micro
Coaxial Micro Helicopter
H. P. Thien, T. Mulyanto, & H. Muhammad
Department of Aeronautics and Astronautics, Faculty of Mechanical and
Aerospace Engineering, Institut Teknologi Bandung, Indonesia
Development of Pose Estimation System Based on Dual Camera
Techniques for Indoor MAV
15:10 - 15:30
Taufiq Mulyanto, M. Luthfi I. Nurhakim and Hari Muhammad
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia.
Coffee Break
15:30 - 16:50
Topic: Flight Physics
15:30 - 15:50
FP-10
Development of Amateur Satellite Ground Station for Education and
Satellite Orbit Determination Independence
Poetro Ridanto Eko and Qadir Amrullah Abdul
Department of Aeronautics and Astronautics, Faculty of Mechanical and
Aerospace Engineering, Institut Teknologi Bandung, Indonesia.
15:50 - 16:10
16:10 - 16:30
16:30 - 16:50
FP-11
FP-12
FP-13
Modeling, Simulation, and Analysis of a Simple Flapping Wing Micro
Aerial Vehicle (FMAV) in Symmetric Level Flight
R.A. Sasongko, Gandi P. Menara, M.A.Moelyadi
Department of Aeronautics and Astronautics, Faculty of Mechanical and
Aerospace Engineering, Institut Teknologi Bandung, Indonesia.
Parametric Study of Half Diamond Wedge Airfoil for NLF Use of
Supersonic Bi-Plane Aircraft in Subsonic Flight
Romie O. Bura, Djoko Sardjadi, Stepen, and Shigeru Obayashi
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia.
Autonomous Navigation for UAV: State of the Art
Hendarko
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia.
16:50 - 18:00
Discussion on future collaboration by AUN/SEED-Net staff
Room
Sixty - Eight Hall
11:00 - 12:20
Topic: Mechanical Systems
11:00 - 11:20
11:20 - 11:40
11:40 - 12:00
12:00 - 12:20
MS-01
MS-02
MS-03
MS-04
Development of Indonesian Gait Database using 2D Optical Motion
Analyzer System
Mahyuddin Andi Isra, Mihradi Sandro, Dirgantara Tatacipta, Moeliono
Marina, Prabowo Tertianto and Maulido Prisanto N.
Faculty of Mechanical and Aerospace Engineering Institute of Technology
Bandung, Indonesia.
Conformity Analysis of Measured Vibration and Sound Signals of
Common Machinery Faults
Kwankhao Sophee, Monika Merdekawati, Pulung Nurprasetio, and Djoko
Suharto
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia.
Control System Design for Optical Stabilization System
Indrawanto and Virdyawan Vani
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia.
A Numerical Study of Cavitation Acting on a Propeller with 5500T Ship –
seriB
12:20 - 13:30
Le Thi Thai, Ngo Ich Long and Le Quang
School of Transportation Engineering, Hanoi University of Science and
Technology, Vietnam.
Lunch (Starlight Restaurant, 11th Floor)
13:30 - 15:10
Topic: Mechanical Systems
13:30 - 13:50
MS-05
Computer Simulation in Root Cause Failure Analysis of Cracks in a
Rotary Steam Dryer Unit
Indra Nurhadi and Hamdzan Asat
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia.
13:50 - 14:10
14:10 - 14:30
14:30 - 14:50
MS-06
MS-07
MS-08
Assessment and Evaluation of Program Outcomes: Experiences of the
School of Mechanical Engineering- Mapua Institute of Technology
Manuel C. Belino and Hans Felix R. Bosshard
School of Mechanical Engineering, Mapua Institute of Technology, Manila,
Philippines.
Analysis And Performance Test Of Compartment Type And Tray Type
Paddy Separator
Lwin Myint Myint
Yangon University Technology, Myanmar.
Feasibility study of Regenerative Hydraulic Braking System for Small Lorry
Vehicle
M. Z. Norhirni and N. A. Mardi
Deparment of Engineering Design and Manufacture, Faculty of Engineering,
University of Malaya, Malaysia.
14:50 - 15:10
MS-09
A Design of an Autonomous Underwater Vehicle
15:10 - 15:30
Phan Anh Tuan and Ngo Van Hien
School of Transportation Engineering, Hanoi University of Science and
Technology, Vietnam.
Coffee Break
15:30 - 16:50
Topic: Mechanical Systems
15:30 - 15:50
MS-10
Geometrical Dimensioning and Tolerancing of Crank Drive Components
of Single Cylinder Diesel Motor
Indra Djodikusumo, Heri Sudarmaji and Pujiyanto
Faculty of Mechanical and Aerospace Engineering Institute of Technology
Bandung, Indonesia.
15:50 - 16:10
16:10 - 16:30
MS-11
MS-12
Estimation of Three-dimensional Tool wear Based on Finite Element
Method
Muhammad Shoaib
N.E.D. University of Engineering & Technology Industrial & Manufacturing
Department, Pakistan.
Calculation of hydrodynamic coefficients of a ship moving in waves
using Indirect Rankine panel method in frequency domain
Nguyen Gia Thang
Ship Design and Shipbuilding Technology Faculty, Vietnam Maritime
University, Vietnam.
16:30 - 16:50
MS-13
A Ship Autopilot Controller Realized with Real-Time UML and MDA
Hien Ngo Van and Tuan Phan Anh
School of Transportation Engineering, Hanoi University of Science and
Technology, Vietnam.
Room
Board room
11:00 - 12:20
Topic: Energy Systems
Chairperson:
11:00 - 11:20
ES-01
The Use of Cow as an Electric and Thermal Power Generation in Remote
Area as a Solution to Realize The Village Self-Reliant Energy Supply
Program in Indonesia
Kamal Samsul
Mechanical and Industrial Engineering Department, Faculty of Engineering,
Gadjah Mada University, Indonesia.
11:20 - 11:40
ES-02
Bio-hydrogen Production from Biodiesel Fuels and Its Application in
SOFCs
Tran Quang-Tuyen, Yusuke Shiratori, Kazunari Sasaki, Nguyen Ngoc Dung,
Iman K. Reksowardojo, and Tirto P. Brodjonegoro
Kyushu University, Japan.
11:40 - 12:00
ES-03
Study on Organic Waste Utilization to Energy in the Lao PDR
Korakanh Pasomsouk and Jaya Seng-Arun
Department of Mechanical Engineering, Faculty of Engineering National
University of Laos, Laos.
12:00 - 12:20
ES-04
Nanostructure of Renewable Oxygenated Fuels Particulate Matter
Karin Preechar, Songsaengchan Yutthana, Laosuwan Songtam and
Charoenphonphanich Chinda
KMITL, Thailand.
12:20 - 13:30
Lunch (Starlight Restaurant, 11th Floor)
13:30 - 15:10
13:30 - 13:50
Topic: Energy Systems
ES-05
Thermal Preference of Filipino College Students from Selected
Universities in Manila
Ko Sherwin, Sante Rainier and Cruz Efren Dela
Mechanical Engineering Department, De La Salle University, Philippines.
13:50 - 14:10
ES-06
Thermal Model Development for Geothermal Steam Pipping System:
Application to SAGS in Wayang Windu Power Plant
Seruni M., Abdurrachim Halim and Riyanto H.
Faculty of Mechanical and Aerospace Engineering, Institute of Technology
Bandung, Indonesia
14:10 - 14:30
ES-07
Efficient Hydrogen Production by Methanol Electrolysis with Proton
Exchange Membrane and Porous Metal Flow Field
Anh Pham Tuan, Tomohiro Baba, Tatsuki Sugiyama and Toshio Shudo
Tokyo Metropolitant University, Japan.
14:30 - 14:50
14:50 - 15:10
ES-08
ES-09
Evaluation of a Diffuser Augmented Horizontal Axis Wind Turbine using
Computational Fluid Dynamics
Martin Ernesto Kalaw, William Hung, Lorens Darin Tan and Jeffrey Christian
Yu
De La Salle University, Philippines.
Design and Construction of Wind Turbine for Rural Area Application
Toe Hla
Department of Physics, University of Yangon, Myanmar.
15:10 - 15:30
Coffee Break
15:30 - 16:50
15:30 - 15:50
Topic: Energy Systems
ES-10
Development of Thermoelectric Module Application for Cooling and
Power Generation
Riyanto Hendi, Martowibowo Sigit Yoewono and Nurprasetio Ignatius Pulung
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia.
15:50 - 16:10
ES-11
Design, Fabrication and Quantification of the Power Produced from a
Power Generating Merry-Go-Round
J. Uy, J. Barrago, N. Calapatia, D. Bautista, M.C.E. Manuel
Faculty, School of Mechanical Engineering, Mapua Institute of Technology,
Philippines.
16:10 - 16:30
ES-12
16:30 - 16:50
ES-13
Characterization of the Solar Drying of Tetraselmis sp. for biofuel
production using a laboratory-scale setup and Statistical Analysis
Lopez Neil Stephen A., Ubando Aristotle T., Biona Manuel M., Tan Raymond
R., Culaba Alvin B., Soledad Garibay, Nieves Toledo, Caridad Jimenez, Ida
Pahila and Letty AmiMechanical Engineering Department, De La Salle
University, Philippines.
Retrofitting an Existing Residential House for Energy Efficiency
and Good Indoor Air Quality
Bruto, D.F., Almonte, C., Cabug, J.E., Gusto, J.B.4 Noche, D.,Manuel, M.C.,
Belino, M.C.
School of Mechanical and Manufacturing Engineering, Mapua Institute of
Technology, Philippines.
Day 2 (Wednesday, 11 January 2012)
Room
Saigon - Hanoi Room
Time
Activities
08:30 - 10:10
08:30 - 08:50
08:50 - 09:10
09:10 - 09:30
09:30 - 09:50
Topic: Aviation
FP-14
Validation experiment of flight path for ballistic ranges system
FP-15
Tung Hoang Thanh, Nguyen Phu Hung, Suzuki Kakuei, Toyoda Atsushi,
Imaizumi Takahiro and Sasoh Akihiro
Deptement of Aeronautical and Space Engineering, Hanoi university of
Science and Technology, Hanoi, Vietnam.
Analysis of Yaw, Pitch and Roll Angles in Gimbals Systems
FP-16
FP-17
Myint Myint Aye, Yin Yin Tun, and Mi Sandar Mon
Mechanical Engineering Department, Yangon Technological University,
Myanmar.
Development of Tunnel in the Sky for Flight Navigation in Indonesia
Airspace
Hisar M. Pasaribu, Javensius Sembiring, and Mahardi Sadono
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia.
Electric RC Model Airplane carrying payload up to 300 grams: Design
and Manufacture
Hieu Ngo Khanh and Huy Bui Khac
Faculty of Transport Engineering, Ho Chi Minh City University of Technology,
Vietnam.
09:50 - 10:10
FP-18
Genetic Algorithm Approach to Solve Helicopter Routing Problem
Operated in Off-shore Location.
10:10 - 10:30
Carry Prameswari, Hisar Pasaribu and Pramudita Satria Palar
Faculty of Mechanical and Aerospace Engineering, Institut Teknologi
Bandung, Indonesia
Coffee Break
10:30 - 12:10
Topic: Structure and Materials
10:30 - 10:50
SM-01
Experimental Study on mechanical behaviors of a Ti 50.93%Ni alloy
under various temperatures
Le Xuan Truong, Tadashige Ikeda and Niwa Masato
10:50 - 11:10
SM-02
Department of Aeronautical and Space Engineering, School of Transportation
Engineering, Hanoi University of Science and Technology, Vietnam.
Damage Characterization in Stitched Composites under Static and
Fatigue Loadings
Yudhanto Arief, Watanabe Naoyuki, Iwahori Yutaka and Hoshi Hikaru
Department of Aerospace Engineering, Tokyo Metropolitan University, Japan.
11:10 - 11:30
11:30 - 11:50
11:50 - 12:10
SM-03
SM-04
SM-05
Investigating Viscoelastic Properties of Composite Beam by Using 3
Point Bending Method
Guo-Wei Ruan, Ming-Chen Chuang, Tuan-Anh Bui, Ching-Tu Lu and NaiShang Liou
Department of Mechanical Engineering, Southern Taiwan University, Taiwan.
Water Absorption Characterization through the Composite Laminate of
Fiberglass/Epoxy produced by Vacuum Assisted Resin Transfer Molding
Syamsudin Hendri, Subawi Handoko and Fadillah Sayyidati Mirah
Faculty of Mechanical and Aerospace Engineering, Institute of Technology
Bandung, Indonesia.
Investigating the Indentation Failure of Sandwich Composite Beam by
Using Bending Tests
12:10 - 13:10
Hsing-Han Yen, Ming-Chen Chuang, Tuan-Anh Bui, Van-Cong Le, Ching-Tu
Lu and Nai-Shang Liou
Department of Mechanical Engineering, Southern Taiwan University, Taiwan.
Lunch (Starlight Restaurant, 11th Floor)
13:10 - 14:50
Topic: Structure and Materials; Aviation
13:10 - 13:30
13:30 - 13:50
SM-06
SM-07
Smoothing Displacement Noisy Data Using Penalized Least Squares
Method
T.H. Dao, I.S. Putra, T. Dirgantara, D. Widagdo and S. Darwis
Faculty of Mechanical and Aerospace Engineering, Institute of Technology
Bandung, Indonesia.
Finite Element Analysis of Sealing Capability of Bolted Flange Joint
To Dara, Sovanna Pan and Nurhadi Indra
Insitute Technology Cambodia, Cambodia.
13:50 - 14:10
14:10 - 14:30
SM-08
SM-09
Structural Analysis of CUA DAT Dam by Numerical Simulation with
Different Contact Modeling between The Concrete Plates and The Dam’s
Body
Hung Viet Nguyen, Khanh Phu Nguyen, Quan Hong Luu, Van Xuan Pham
Center for Development and Application of Software for Industry, Hanoi
University of Science and Technology, Vietnam.
A Finite Volume Method That Controls Vorticity Based on the LimitedRotated-Richtmyer Scheme
Farzad Ismail
School of Aerospace Engineering, Universiti Sains Malaysia, Malaysia.
14:30 - 14:50
SM-10
Dynamic Simulation of Split Hopkinson Pressure Bar
Gunawan Leonardo, Sitompul Sahril A., Dirgantara Tatacipta and Putra
Ichsan Setya
Faculty of Mechanical and Aerospace Engineering, Institute of Technology
Bandung, Indonesia.
Coffee Break
14:50 - 15:10
Room
Sixty - Eight Hall
08:30 - 10:10
08:30 - 08:50
Topic: Mechanical Systems
MS-14
Design and Analysis of Stiffness on Spindle Shaft for High Precision
Milling Machine
Aung Hein Latt
Department of Mechanical Engineering, Mandalay Technological University,
Myanmar.
08:50 - 09:10
09:10 - 09:30
09:30 - 09:50
09:50 - 10:10
MS-15
MS-16
MS-17
MS-18
A Design of Propeller for a High Speed Ship
Phan Anh Tuan and Phan Thi Thanh Huong
School of Transportation Engineering, Hanoi University of Science and
Technology, Vietnam.
Design and Strength Analysis of Tool Pots for Shelftype Tool Storage
Magazine in Machining Centre
Swe Nyunt Zin
Department of Mechanical Engineering Mandalay Technological University,
Myanmar.
Aerodynamic Lift and Drag of Cascaded Delta Wings in Water Tunnel at
Various Wings Configurations
Sutrisno Ir and Mendrofa F.I.
Mechanical and Industrial Engineering Department Gadjah Mada University,
Indonesia
Analysis of Euler Angles in a Simple Two-Axis Gimbals Set
10:10 - 10:30
Myint Myint Aye, Yin Yin Tun, and Mi Sandar Mon
Mechanical Engineering Department, Yangon Technological University,
Myanmar.
Coffee Break
10:30 - 12:10
Topic: Fluid Dynamics
10:30 - 10:50
FD-01
10:50 - 11:10
FD-02
11:10 - 11:30
FD-03
Application of a sensitivity equation method to the turbulent flow around
the complex geometriesDinh Cong Truong, Vu Duy Quang, and Hoang Thi
Kim DungSchool of Transportation Engineering, Hanoi University of Science
and Technology, Vietnam.
Study of Flow on a Flat Plate with Partly Laminar and Partly Turbulent
Boundary Layer
Amalia Ema
Flight Physics Research Group – Aeronautics and Astronautics Study
Program, Faculty of Mechanical and Aerospace Engineering, Indonesia.
Coanda Jet Lift Enhancement: Two-Dimensional Computational Studies
Harijono Djojodihardjo and Hamid M.Faisal Abdul
Department of Aerospace Engineering, Universiti Putra Malaysia, Malaysia.
11:30 - 11:50
11:50 - 12:10
FD-04
FD-05
Boundary Element Method for Satisfying Boundary Conditions in
Viscous Vortex Methods
Dung Duong Viet, Zuhal Lavi R. and Muhamad Hari
Faculty of Mechanical and Aerospace Engineering Institute of Technology
Bandung, Indonesia.
CFD Simulation of the Compressor and the Turbine of Turbojet 500 N
12:10 - 13:10
Firman Hartono and Ahmad Jamaludin Fitroh
Faculty of Mechanical and Aerospace Engineering Institute of Technology
Bandung, Indonesia.
Lunch (Starlight Restaurant, 11th Floor)
13:10 - 14:50
Topic: Fluid Dynamics
13:10 - 13:30
13:30 - 13:50
13:50 - 14:10
14:10 - 14:30
14:30 - 14:50
FD-06
FD-07
FD-08
FD-09
FD-10
Numerical Simulation for Supercritical Fluid in the Supersonic Nozzle
Using Real Gas Effect
Albert Meigo R.E.Y, Romie O. Bura and Bambang K. Hadi
Faculty of Mechanical and Aerospace Engineering Institute of Technology
Bandung, Indonesia.
Visualization of Flow Patterns and Measurement of Void Fraction in AirWater Two-Phase Flow
Mohd Zamri Zainon, Rahizar Ramli and Mohd Ardan Zubir
Department of Mechanical Engineering, Faculty of Engineering, University of
Malaya, Malaysia.
Development of Monte Carlo Method for Solar Radiative Heat Transfer
and Daylighting Computation
Riyanto Hendi
Faculty of Mechanical and Aerospace Engineering Institute of Technology
Bandung, Indonesia.
Characteristics of a Delta Wing Flow
Hoang Thi Kim Dung and Yoshiaki Nakamura
Department of Aeronautical and Space Engineering Hanoi University of
Science and Technology, Vietnam.
Development of a 3-D Comprssible Reynolds Averaged Navier-Stoke
Solver
Nguyen Anh Thi, Nguyen Hoang Tuan, and Tran Thanh Tinh
Department of Aeronautical Engineering, VNU-HCM, Vietnam.
14:50 - 15:10
Coffee Break
Room
Board room
Time
Activities
08:30 - 10:10
08:30 - 08:50
08:50 - 09:10
Topic: Thermal Engineering
TE-01
TE-02
A Simulation Study on Performance Characteristics of an Agricultural
Small Diesel Engine by AVL Boost
Phan The Anh, Chiem Tran Lam, Tran Tien Dat, Huynh Thanh Cong
VNU-HCMC Key Lab for Internal Combustion Engine, HCMUT, Vietnam.
Effects of Using Blend Coconut Oil on Characteristics of a DirectInjection Compression-Ignition Engine
Vo Tan Chau, Truong Hoai Linh, Phung Minh Loc, and Nguyen Ngoc Dung
VNU-HCMC Key Lab for Internal Combustion Engine, HCMUT, Vietnam.
09:10 - 09:30
09:30 - 09:50
TE-03
TE-04
Performance, Emissions of Pure Plant Oils (PPO) fuelled a Low Speed
Indirect Injection Diesel Engine
Reksowardojo Iman Kartolaksono, Doan Dinh Khac, Surjana Nana,
Soerawidjaja Tatang H., Kilgour Alton J., Brodjonegoro Tirto P. and
Arismunandar Wiranto
Faculty of Mechanical and Aerospace Engineering, Institute of Technology
Bandung, Indonesia.
Simulation and experimental studies of performance of 110cc
motorcycle engine running on biogas
Ga Bui Van, Tung Tran Thanh Hai and Dong Nguyen Van
The University of Danang, Vietnam.
09:50 - 10:10
TE-05
Development of a DME fuelled HCCI Engine
Wattanavichien Kanit
Chulalongkorn University, Thailand.
10:10 - 10:30
Coffee Break
10:30 - 12:10
10:30 - 10:50
Topic: Thermal Engineering
TE-06
An Experimental Investigation of Performance Characteristics of
Agricultural Diesel 12.5HP Engine
Lam Chiem Tran, Phuong Vo Le Hoai, Anh Phan The, Long Tran Dang, Cong
Huynh Thanh, Hung Le Viet and Chanh Nguyen Ngoc
VNU-HCMC Key Lab for Internal Combustion Engine, HCMUT, Vietnam.
10:50 - 11:10
TE-07
Analysis of Water Cooling for Ground-tested Liquid Propellant Rocket
Engines
Nan Oo
Mechanical Engineering Department,
Mandalay Technology University, Mandalay, Myanmar
11:10 - 11:30
11:30 - 11:50
11:50 - 12:10
TE-08
TE-09
TE-10
Statistical Analysis to Determining the Effect of Diesel-Ethanol Blending
on Stationary Indirect Injection Diesel Engine Performance
Reksowardojo Iman Kartolaksono, Nur Arifin, Santoso W.B. and Putrasarib Y.
Faculty of Mechanical and Aerospace Engineering, Institute of Technology
Bandung, Indonesia.
Performance and Emission Characteristics of a DI Diesel Engine by
Using Mixed Biodiesel Fuels
Vo Tan Chau, Vo Le Hoai Phuong, Nguyen Quoc Tan and Nguyen Ngoc
Dung
VNU-HCMC Key Lab for Internal Combustion Engine, HCMUT, Vietnam.
Study on Performance and Emission Characteristics of Gasoeus Fuelled
Motorcycle
Truong Hoai Linh, Tran Dang Long and Nguyen Ngoc Dung
VNU-HCMC Key Lab for Internal Combustion Engine, HCMUT, Vietnam.
12:10 - 13:10
Lunch (Starlight Restaurant, 11th Floor)
13:00 - 16:50
13:10 - 13:30
Topic: Flight Physics, Structure and Material, CFD
FP-19
Attitude Stabilization of Quadrotor-typed Aircraft
Tran Dang Long, Nguyen Vinh Hao, and Nguyen Anh Thi
VNU-HCMC Key Lab for Internal Combustion Engine, HCMUT, Vietnam.
13:30 - 13:50
13:50 - 14:10
14:10 - 14:30
SM-11
SM-12
FD-11
Application of the Smooth Particle Hydrodynamics method for high
velocity impact simulation
Quoc Huy Vu, Anh Tuan Le and Phu Khanh Nguyen
Department of Aeronautical and Space Engineering, Hanoi University of
Science and Technology, Vietnam.
An experimental method for evaluating the accuracy of camera
calibration toolbox developed by Bouguet
Phuc Tran Van, Putra I.S., Dirgantara T. and Mihradi S.
Faculty of Mechanical and Aerospace Engineering, Institute of Technology
Bandung, Indonesia.
Farfield-based Aerodynamic Forces Determination
Nguyen Chi Hieu and Nguyen Anh Thi
Department of Aeronautical Engineering, VNU-HCM, Vietnam.
14:30 - 14:50
14:50 - 15:10
MS-19
Tolerance Analysis And Optimization Design Of Mechanical Products
Using Monte Carlo Simulation
Tuan Pham Minh, Tuan Nguyen Hoang Anh, Loc Nguyen Huu
Faculty of Mechanical Engineering, Ho Chi Minh City University of
Technology, Vietnam.
Coffee Break
TABLE OF CONTENTS
Presentation No
Title and Authors
Page
FD-01
Application of a sensitivity equation method to the turbulent flow
around the complex geometries
Cong Truong Dinh and Duy Quang Vu, and Thi Kim Dung Hoang
1
FD-02
Study of Flow on a Flat Plate with Partly Laminar and Partly
Turbulent Boundary Layer
Ema Amalia
9
FD-03
Coanda Jet Lift Enhancement: Two-Dimensional Computational
Studies
Harijono Djojodihardjo and Hamid M.Faisal Abdul
Boundary Element Method for Satisfying Boundary Conditions in
Viscous Vortex Methods
Viet Dung Duong and Lavi R. Zuhal
17
CFD Simulation of the Compressor and the Turbine of Turbojet
500 N
Firman Hartono and Ahmad Jamaludin Fitroh
Numerical Simulation for Supercritical Fluid in the Supersonic
Nozzle Using Real Gas Effect
Albert Meigo R.E.Y, Romie O. Bura and Bambang K. Hadi
34
FD-07
Visualization of Flow Patterns and Measurement of Void Fraction
in Air-Water Two-Phase Flow
Mohd Zamri Zainon, Rahizar Ramli and Mohd Ardan Zubir
49
FD-08
Development of Monte Carlo Method Application for Solar
Radiative Heat Gain and Daylighting Computation
Hendi Riyanto
57
FD-09
Characteristics of a Delta Wing Flow
Dung Hoang Thi Kim and Yoshiaki Nakamura
64
Topic 1: Fluid Dynamic
FD-04
FD-05
FD-06
27
41
Topic 2: Energy System and Thermal Engineering
ES-01
The Use of Cow as an Electric and Thermal Power Generation in
Remote Area as a Solution to Realize The Village Self-Reliant
Energy Supply Program in Indonesia
Samsul Kamal
71
ES-02
Bio-hydrogen Production from Biodiesel Fuels and Its
Application in SOFCs
Tran Quang-Tuyen, Yusuke Shiratori, Kazunari Sasaki, Nguyen Ngoc
Dung, Iman K. Reksowardojo, and Tirto P. Brodjonegoro
Study on Organic Waste Utilization to Energy in the Lao PDR
Korakanh Pasomsouk and Jaya Seng-Arun
Nanostructure of Renewable Oxygenated Fuels Particulate
Matter
Preechar Karin,Yutthana Songsaengchan, Songtam Laosuwan and
Chinda Charoenphonphanich
Thermal Preference of Filipino College Students from Selected
Universities in Manila
Sherwin Ko, Rainier Sante and Efren Dela Cruz
77
ES-03
ES-04
ES-05
84
89
96
Presentation No
ES-06
ES-07
ES-08
ES-09
Title and Authors
Thermal Model Development for Geothermal Steam Pipping
System
Seruni M., Abdurrachim H. and Riyanto H.
Efficient Hydrogen Production by Methanol Electrolysis with
PEM and Porous Metal Flow Field
Anh Pham Tuan, Tomohiro Baba, Tatsuki Sugiyama and Toshio
Shudo
Evaluation of a Diffuser Augmented Horizontal Axis Wind
Turbine using Computational Fluid Dynamics
Wendell-Harris Chan, William Hung, Lorens Darin Tan, Jeffrey
Christian Yu and Martin Ernesto Kalaw
Page
100
105
112
Design and Construction of Wind Turbine for Rural Area
Application
Hla Toe, Win Win Thar, Tin Maung Tun and Ko Ko Kyaw Soe
Development of Thermoelectric Application for Cooling and
Power Generation
Hendi Riyanto, Sigit Yoewono Martowibowo and Ignatius Pulung
Nurprasetio
Design, Fabrication and Quantification of the Power Produced
from a Power Generating Merry-Go-Round
J. Uy, J. Barrago, N. Calapatia, D. Bautista, M.C.E. Manuel
120
Characterization of the Solar Drying of Tetraselmis sp. for
biofuel production using a laboratory-scale setup and Statistical
Analysis
LOPEZ, Neil Stephen A., UBANDO, Aristotle T., BIONA, Manuel M.,
TAN, Raymond R., CULABA, Alvin B., GARIBAY, Soledad S.,
TOLEDO, Nieves A., JIMENEZ, Caridad N., PAHILA, Ida G. and AMI,
Letty S.
Retrofitting an Existing Residential House for Energy Efficiency
and Good Indoor Air Quality
Bruto, D.F., Almonte, C., Cabug, J.E., Gusto, J.B., Noche, D.
136
Highly Efficient Biomass Utilization with Fuel Cell Technology
Yusuke Shiratori, Tuyen Tran Quang and Kazunari Sasaki
A Simulation Study on Performance Characteristics of an
Agricultural Small Diesel Engine by AVL Boost
Phan The Anh, Chiem Tran Lam, Tran Tien Dat, Huynh Thanh Cong
151
Effects of Using Blend Coconut Oil on Characteristics of a
Direct-Injection Compression-Ignition Engine
Vo Tan Chau, Truong Hoai Linh, Phung Minh Loc, Nguyen Ngoc
Dung
Performance, Emissions of Pure Plant Oils (PPO) fuelled a Low
Speed Indirect Injection Diesel Engine
Iman K. REKSOWARDOJO, Doan Khac DINH, Nana SURJANA,
Athol James KILGOUR, Tirto P. BRODJONEGORO, Tatang H.
SOERAWIDJAJA, Wiranto ARISMUNANDAR
163
TE-04
Simulation and experimental studies of perfomance of 110cc
motorcycle engine running on biogas
Ga Bui Van, Tung Tran Thanh Hai and Dong Nguyen Van
182
TE-05
Development of a DME fuelled HCCI Engine
Kanit Wattanavichien
191
ES-10
ES-11
ES-12
ES-13
ES-14
TE-01
TE-02
TE-03
125
132
144
159
172
Presentation No
TE-06
TE-07
TE-08
TE-09
TE-10
Title and Authors
A Preliminary Investigation of Performance Characteristics of
Agricultural Diesel 12.5HP Engine
Chiem Tran Lam, Vo Le Hoai Phuong, Phan The Anh, Tran Dang
Long, Huynh Thanh Cong, Le Viet Hung and Nguyen Ngoc Chanh
Analysis of Water Cooling for Ground Test Liquid Propellant
Rocket Engines
Nan Oo
Statistical Analysis to Determining the Effect of Diesel-Ethanol
Blending on Stationary IDI Diesel Engine Performance
Iman Kartolaksono Reksowardojo, Arifin Nur, W.B. Santoso, Y.
Putrasari
Performance and Emission Characteristics of a DI Diesel Engine
by Using Mixed Biodiesel Fuels
Vo Tan Chau, Vo Le Hoai Phuong, Nguyen Quoc Tan and Nguyen
Ngoc Dung
Study on Performance and Emission Characteristics of Gasoeus
Fuel Motorcycle
Truong Hoai Linh, Tran Dang Long and Nguyen Ngoc Dung
Page
199
205
211
219
226
3. Mechanical Systems
MS-01
Development of Indonesian Gait Database using 2D Optical
Motion Analyzer System
Andi Isra MAHYUDDIN, Sandro MIHRADI, Tatacipta DIRGANTARA,
Marina MOELIONO, Tertianto PRABOWO, Prisanto N. MAULIDO
232
MS-02
Conformity Analysis of Measured Vibration and Sound Signals
of Common Machinery Faults
Kwankhao Sophee, Monika Merdekawati, Pulung Nurprasetio, and
Djoko Suharto
Control System Design for Optical Stabilization System
Indrawanto and Vani Virdyawan
240
A Numerical Study of Cavitation Acting on a Propeller with 5500T
- SeriB Ship
Le Thi Thai, Le Quang and Ngo Ich Long
Computer Simulation in Root Cause Failure Analysis
of Cracks in a Rotary Steam Dryer Unit
Indra Nurhadi and Hamdzan Asat
250
MS-06
Assessment and Evaluation of Program Outcomes: Experiences
of the School of Mechanical Engineering
Manuel C. Belino and Hans Felix R. Bosshard
263
MS-07
Analysis And Performance Test Of Compartment Type And Tray
Type Paddy Separator
Myint Myint Lwin
267
MS-08
Feasibility study of Regenerative Hydraulic Braking System for
Small Lorry Vehicle
M. Z. Norhirni and N. A. Mardi
274
MS-09
A Design of an Autonomous Underwater Vehicle
Phan Anh Tuan and Ngo Van Hien
Geometrical Dimensioning and Tolerancing
of Crank Drive Components of Single Cylinder Diesel Motor
Indra Djodikusumo, Heri Sudarmaji and Pujiyanto
283
MS-03
MS-04
MS-05
MS-10
245
256
289
Presentation No
MS-11
MS-12
MS-13
Title and Authors
Estimation of Three-dimensional Tool wear Based on Finite
Element Method
Muhammad Shoaib
Calculation of hydrodynamic coefficients of a ship moving in
waves using Indirect Rankine panel method in frequency domain
Nguyen Gia Thang
Page
297
301
A Ship Autopilot Controller Realized with Real-Time UML and
MDA
Ngo Van Hien and Phan Anh Tuan
Design and Analysis of Stiffness on Spindle Shaft for High
Precision Milling Machine
Aung Hein Latt, Swe Zin Nyunt and Theingi
309
A Design of Propeller for a High Speed Ship
Phan Anh Tuan and Phan Thi Thanh Huong
Design and Strength Analysis of Tool Pots for Shelf Type Tool
Storage Magazine in Machining Centre
Swe Zin Nyunt, Aung Hein Latt and Theingi
322
MS-17
Aerodynamic Lift and Drag of Cascaded Delta Wings in Water
Tunnel at Various Wings Configurations
Sutrisno and F.I. Mendrofa
335
MS-18
Analysis of Euler Angles in a Simple Two-Axis Gimbals Set
Myint Myint Aye, Yin Yin Tun and Mi Sandar Mon
Tolerance Analysis And Optimization Design Of Mechanical
Products Using Monte Carlo Simulation
Tuan Pham Minh, Tuan Nguyen Hoang Anh, Loc Nguyen Huu
343
MS-14
MS-15
MS-16
MS-19
316
328
350
4. Structure and Materials
SM-01
Experimental Study on Thermo-mechanical Behaviors of a Ti
50.93%Ni Alloy under Various Temperatures
Le Xuan Truong, Tadashige IKEDA and Niwa MASATO
357
SM-02
Damage Characterization in Stitched Composites under Static
and Fatigue Loadings
Arief Yudhanto, Naoyuki Watanabe, Yutaka Iwahori and Hikaru
Hoshi
Investigating Viscoelastic Properties of Composite Beam by
Using 3 Point Bending Method
Guo-Wei Ruan, Ming-Chen Chuang, Tuan-Anh Bui, Ching-Tu Lu and
Nai-Shang Liou
Water Absorption Characterization through the Composite
Laminate of Fiberglass/Epoxy produced by Vacuum Assisted
Resin Transfer Molding
Hendri Syamsudin, Handoko Subawi and Sayyidati Mirah Fadillah
Investigating the Indentation Failure of Sandwich Composite
Beam by Using Bending Tests
Hsing-Han Yen, Ming-Chen Chuang, Tuan-Anh Bui, Van-Cong Le,
Ching-Tu Lu and Nai-Shang Liou
361
Smoothing Displacement Noisy Data Using Penalized Least
Squares Method
T.H. Dao, I.S. Putra, T. Dirgantara, D. Widagdo and S. Darwis
Finite Element Analysis of Sealing Capability of Bolted Flange
Joint
378
SM-03
SM-04
SM-05
SM-06
SM-07
367
370
375
383
Presentation No
SM-08
Title and Authors
To Dara, Pan Sovanna and Indra Nurhadi
Page
Structural Analysis of CUA DAT Dam by Numerical Simulation
with Different Contact Modeling between The Concrete Plates
and The Dam’s Body
Hung Viet NGUYEN, Khanh Phu NGUYEN, Quan Hong LUU, Van
Xuan PHAM
A Finite Volume Method That Controls Vorticity Based on the
Limited-Rotated-Richtmyer Scheme
Farzad Ismail
390
SM-10
Dynamic Simulation of Split Hopkinson Pressure Bar
Leonardo Gunawan, Sahril Afandi Sitompul, Tatacipta Dirgantara and
Ichsan Setya Putra
401
SM-11
Application of the Smooth Particle Hydrodynamics method for
high velocity impact simulation
Quoc Huy Vu, Anh Tuan Le and Phu Khanh Nguyen
408
SM-12
An experimental method for evaluating the accuracy of camera
calibration toolbox developed by Bouguet
P.V. Tran, I.S. Putra, T. Dirgantara, S. Mihradi
416
SM-09
395
5. Flight Physics and Aviation
FP-01
Evaluation of Airfoils that Suitable for a Forward Swept Wing
Ema Amalia
Numerical Simulation of Vortical Flow on High Attack Angle of
Delta Wing using RANS
M. Nurrachman, Romie O. Bura and Albert Meigo R.E.Y
423
FP-03
High Angle-of-Attack Flight Dynamics Analysis Using Bifurcation
and Continuation Approach
Hendarko
434
FP-04
Estimation of Aerodynamic Parameter of Micro Aerial Vehicle
Using Total Least Squares
H. Muhammad, H. P. Thien and T. Mulyanto
441
FP-05
Pseudo-shock wave generating by a strut abruptly inserting into
a supersonic flow inside rectangular duct
Nguyen Phu Hung, Naoki NAKASHIMA and Akia UMEMURA
448
FP-06
Development of a Wind Tunnel Test Equipment for 3 DoF
Aeroelastic Experimental Studies
R.A. Sasongko, M. Akbar, F.S. Pranoto and Pramudita S. P.
452
FP-07
Drag Minimization of Low Reynolds Number Airfoil Using Single
Objective Particle Swarm Optimization
Pramudita S. Palar, Arief Hafizuddin, Dung Duong Viet and Lavi
R.Zuhal
Modeling and Identification of Longitudinal Dynamic Model of
Micro Coaxial Micro Helicopter
H. P. Thien, T. Mulyanto and H. Muhammad
459
Development of Pose Estimation System Based on Dual Camera
Techniques for Indoor MAV
Taufiq Mulyanto, M. Luthfi I. Nurhakim and Hari Muhammad
476
FP-02
FP-08
FP-09
429
468
Presentation No
FP-10
Title and Authors
Development of Amateur Satellite Ground Station for Education
and Satellite Orbit Determination Independence
Ridanto Eko Poetro and Amrullah Abdul Qadir
Page
484
FP-11
Modeling, Simulation, and Analysis of a Simple Flapping Wing
Micro Aerial Vehicle (FMAV) in Symmetric Level Flight
R.A. Sasongko, Gandi P. Menara, M.A.Moelyadi
490
FP-12
Parametric Study of Half Diamond Wedge Airfoil for NLF Use of
Supersonic Bi-Plane Aircraft in Subsonic Flight
Romie O. Bura, Djoko Sardjadi, Stepen, and Shigeru Obayashi
498
FP-13
Autonomous Navigation for Unmanned Aerial Vehicle: State of
the Art
Hendarko
Validation experiment of flight path for ballistic ranges system
Hoang Thanh Tung, Nguyen Phu Hung, Kakuei Suzuki, Atsushi
Toyoda, Takahiro Imaizumi and Akihiro Sasoh
506
Analysis of Yaw, Pitch and Roll Angles in Gimbals Systems
Aye Myint Myint, Yin Yin Tun and Mi Sandar Mon
Genetic Algorithm Approach to Solve Helicopter Routing
Problem Operated in Off-shore Location
Hisar Pasaribu, Carry Prameswari and Pramudita Satria
514
FP-17
Electric RC Model Airplane carrying payload up to 300 grams:
Design and Manufacture
Ngo Khanh Hieu and Bui Khac Huy
528
FP-18
Development of Tunnel in The Sky for Flight Navigation in
Indonesian Airspace
Hisar M. Pasaribu, Javensius Sembiring, and Mahardi Sadono
534
FP-14
FP-15
FP-16
510
520
The 4th AUN/SEED-Net RC MeAe 2012
January 10-11, 2012, HCMUT, Vietnam
Drag Minimization of Low Reynolds Number Airfoil Using
Single Objective Particle Swarm Optimization
1
Pramudita S. Palar , Lavi R.Zuhal
1
1
Flight Physics Research Group, Faculty of Mechanical and Aerospace Engineering
Institut Teknologi Bandung, Jalan Ganesha 10, Bandung 40132, Indonesia
Abstract
One of typical scenario in low Reynolds number airfoil optimization is to find the geometry that
has minimum drag coefficient in specified design condition with respect to the initial airfoil. To
systematically minimize the drag of base airfoil, Particle Swarm Optimization (PSO) which is based on
swarm intelligence is employed as a method that iteratively trying to improve the candidate of airfoils until
it finds the new optimized airfoil. In this paper, airfoil is generated by 16 points B-spline curves with XFOIL
solver as a tool to obtain the aerodynamic performance of generated airfoil. PSO systematically altered
the control points position with respect to the initial airfoil as a base design. Results show that the
developed PSO is able to find satisfactory optimized airfoil in term of minimizing drag coefficient without
any degradation on other aerodynamic performance (lift and moment coefficient). Therefore, PSO has a
great potential to be used and improved as a design and optimization tool for low Reynolds number airfoil.
Keywords: Airfoils, Low Reynolds Number, Particle Swarm Optimization, B-spline, XFOIL
1. Introduction
1.1
Optimization of low Reynolds Number
Airfoil
The challenge in designing airfoils that
operate in low Reynolds number is the existence
of phenomenon such as laminar separation
bubbles that leads to excessive drag and low
maximum lift. Special airfoils that have high
performance aerodynamic characteristic to be
applied in this flow regime are designed to address
this problem instead of using existing airfoil [1].
S1223 airfoil is the example of airfoil that is
designed to have high lift characteristic in low
Reynolds number application. Nonetheless, S1223
airfoil suffers the problem of large value of drag in
spite of its high lift. Airfoil optimization procedure is
usually performed by altering the initial geometry
of base airfoil to achieve optimized airfoil that has
better characteristic aerodynamic performance.
maximization of the efficiency of lift to drag ratio
(Cl/Cd).
In
optimizing
the
aerodynamic
performance, the optimization goal can be in the
form of single objective or multiple objectives by
approximating the optimal trade-off between
objective function. Take an example of the airfoil
optimization problem that takes account lift and
drag coefficient as the objective function. The
objective functions can be combined into single
objective form of lift to drag ratio (Cl/Cd) or
approximating the so called pareto-frontier sets
which is formed by the optimal trade-off between
Cl and Cd. Non-gradient based heuristics
optimization methods are famous due to its
advantage of higher probability to find the true
global optimum of optimization problems
compared to standard gradient methods. This
paper considers the minimization of drag using
Particle Swarm Optimization (PSO) method as a
tool to discover the optimized airfoil.
1.2
Figure 1: Shape profile of S1223 Airfoil
Common scenario in airfoil optimization is
the maximization of lift coefficient (Cl),
minimization of drag coefficient (Cd), or the
Particle Swarm Optimization
PSO is an optimization method based on the
principle of social behavior and information
exchange between individuals in swarm formation
such as bird flocking and fish schooling. It works
by iteratively trying to improve the candidate of
solutions based on the quality of each candidate
solution. From the perspective of the mathematical
modeller, "flocking" is the collective motion of a
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The 4th AUN/SEED-Net RC MeAe 2012
January 10-11, 2012, HCMUT, Vietnam
large number of self-propelled entities and is a
collective animal behavior exhibited by many living
beings such as birds, fish, bacteria, and insects
[2]. It is considered an emergent behavior arising
from simple rules that are followed by individuals
and does not involve any central coordination.
PSO is first developed by Kennedy and
Eberhart in 1995 ([3],[4]) and start to find its
application in many engineering optimization
problem ([5],[6]). Just like other stochastic method
such as Genetic Algorithm, PSO doesn’t need any
gradient information on the optimization process
so it can solve problems with non-differentiable
characteristic. Other similarities shared between
PSO and GA is that both of the algorithms are
initialized with random solutions and work with
population of solutions. To discover the point of
optimality, the solutions in PSO (called particle)
move through the problem space where exchange
of information between particles is the critical point
for the swarm to find the optima.
Figure 2: Swarm in nature, bird flocking (left), fish schooling
(right)
A B-spline of degree k is a parametric curve:
(2)
Which is composed by a linear combination of
basis B-splines Bi,k of degree k
(3)
The points Pi are called control points or de Boor
points. There are m-k+1 control points and they
are form a convex hull. The m-k+1 basis B-splines
of degree k can be defined by Cox-de Boor
recursion formula [7]
(4)
Fig.3 depicts an example of how
combination of control points creates the shape of
airfoil. This work uses 16 control points to
formulate the geometry where 3 points are located
near trailing edges, 10 points between trailing and
leading edge, and 3 points near leading edges.
The points in fig.3 are the location of control points
in Euclidean frame where the red line is the
reproduced airfoil geometry extrapolated by given
de Boor control points.
2. Methods
2.1 B-spline shape function
To generate airfoil geometry, B-spline
shape function based on a set of control points is
used to reproduce the initial shape of airfoil and
also become the decision vector of the
optimization
scheme.
B-spline
method
extrapolates a curve from given control points with
respect to a given degree k where the geometry of
the airfoil can be altered by tuning the position of
control points. The shape of given airfoil is able to
be reproduced by well-adjustment of the control
points until the shape of B-spline generated airfoil
is fairly close to the defined shape of target airfoil.
Given m real values ti, called knots, with:
(1)
Figure 3: De Boor control points and generated airfoil curve
2.2 XFOIL Solver
XFOIL is used to calculate the
aerodynamic characteristic of low Reynolds
number airfoil as a tool to obtain the objective
function value in present work. XFOIL uses a
linear-vorticity panel method for inviscid analysis
coupled with an integral boundary-layer method
for viscous analysis [8]. In population based
optimization algorithm where the number of
function evaluation could be so large, XFOIL
provides quick computing time which is suitable
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The 4th AUN/SEED-Net RC MeAe 2012
January 10-11, 2012, HCMUT, Vietnam
to be nested inside PSO. XFOIL is called every
time the PSO algorithm needs fitness value to
determine the action that will be taken by the
particles. Every simulation was conducted using
230 panels to discretize and predict the
aerodynamic performance of the airfoil.
2.3 Particle Swarm Optimization operations
Each particle in population represents
unique solution as a vector of real number that can
exist in multi-dimensional and hyper volume of
search space. Every particle stores the information
of previous velocity, best previous position, and
the best previous position of its neighborhood
which are used to determine its current velocity.
The previous velocity term stands as inertia
component, the previous best position stands as
personal influence component, and the best
previous best position of the neighborhood
constitutes the social influence component of the
iteration. Each particle updates its velocity and
position for the next generation using following
equation:
exploration. Linear inertia reduction technique is
applied by linearly reducing the inertia weight from
0.9 at first generation to 0.4 at last generation. By
applying linear inertia reduction, PSO explores the
search space in the beginning of optimization
process and gradually switch to exploit the search
space toward the end of search process. The
swarm topology used in this work is fully
connected topology where all particles are
connected to each other and share one global best
information (left figure in fig. 5). The advantage of
PSO is that the method only has few parameters
to adjust but able to solve wide variety of problems
and application with only few adaptations.
In our work, each particle represents the
position of control points that govern the geometry
of airfoil. To obtain the fitness value of particles at
current generation, XFOIL solver is used to obtain
the value of aerodynamic characteristics such as
Cl and Cd where this information is used to
determine the behavior of particles toward optima.
(6)
(7)
Where
is the position of particle at
generation t,
is the best position achieved by
particle until generation t, and
is the best
position of the neighborhood of the
particle until
generation t.
and
are termed as local
and global best component, respectively. Both of
local best and global best component for each
particle are updated only on each generation if the
function value obtained by each solution in current
generation is better than the previous generation.
and
is the n-dimensional random vectors,
where n is the number of particle, that generated
by uniform distribution. c1 and c2 are called
cognitive and social parameter, respectively,
where both of these parameters control the
dominance of personal or social component to
each other. Information of best and global fitness
achieved by each particle and its neighborhood
are also stored but only used for updating the local
and global best component. The parameter
is called the inertia weight to control the
exploration and exploitation ability of particle
swarm
where
larger
inertia
encourages
Figure 4: Illustration of how PSO determines the new particle
location
Figure 5: Topologies in PSO: Fully connected (left), local best
(middle), Von Neumann (right)
3. Performance Validation of developed PSO
code
A numbers of test function are used to test
the performance of developed PSO to test its
capabilities to be applied in a range of optimization
problem. Several classes of test function
considered in this work including:
(a) Unimodal / Multimodal
(b) Two-dimensional / Multidimensional
(c) Small / huge number of local extremes
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(d) Evenly / unevenly distributed local extremes
Six test functions that include above
characteristics of unimodal, multimodal, and hyperdimensionality were used as test problems. Since
the optimization problem in this work deals with up
to 16 decision variables, the PSO needs to be
tested in hyper-dimensional case to see the
capabilities of developed PSO on finding the
optimum solutions in this work. All functions are
then tested in 30 dimensional decision variables.
PSO parameters were set to the following value:
c1 = c2 = 1.4691, N = 20 (Amount of particles),
wi(t) reduce linearly from 0.9 to 0.4 from the first to
last iteration, and maximum generation = 5000.
Result on table 1 shows the average best function
value over 30 trials and its standard deviation. The
history of convergence versus average best value
is also shown on fig.6, 7, and 8.
Test function
Dim
Variable
Global
Average
Standard
range
optimum
Best
Deviation
value
Value
Dejong F1
30
[-100 100]
0
3.97E-11
2.94E-10
Rotated
30
[-100 100]
0
3.81E-11
2.11E-10
Dejong F3
30
[-5.12 5.12]
-180
-180
0
Dejong F4
30
[-1.28 1.28]
0
4.50E-28
4.21E-27
Schwefel
30
[-500 500]
-12569.5
1.26E+0
4
11.8438
Griewank
30
[-600 600]
0
0.0071
0.0084
Hyper
Elipsoid
Table 1: Result of developed PSO algorithm
Result shows that the developed PSO is
able to find the global optimum of all test function
in all 30 trials. By seeing the result of the
st rd th
developed PSO in De Jong 1 ,3 ,4 and Rotated
Hyper Ellipsoid function, it can be concluded that
the PSO is able to deal with discontinuity and
noisy function. Even in very high dimensional and
highly multimodal complex function such as
Schwefel and Griewank, PSO can find the
solutions near global optimum in all trials with
small standard deviation. Based on this result, it is
confident to say that the developed PSO can be
applied for single-objective airfoil optimization case
in this work.
Figure 6: PSO convergence performance in De Jong 1st (left)
and Rotated Hyper Ellipsoid (right) function
4. Drag Minimization of Low Reynods Number
airfoil: S1223 Airfoil
Figure 7: PSO convergence performance in De Jong 3rd (left)
and De Jong 4th (right) function
Figure 8: PSO convergence performance in Schweffel (left) and
Griewank (right) function
S1223 airfoil is an airfoil that is specifically
designed for Low Reynolds number application.
Generally, S1223 airfoil is a high performance
airfoil with high lift characteristic in low Reynolds
number but suffers from large drag [9]. Based on
this information, the main objective is to minimize
drag
coefficient
without
any
significant
deterioration from the original characteristic.
Therefore, optimization was performed in this work
to see how S1223 airfoil can be improved to
achieve lower drag coefficient without any
degradation in other aerodynamic performance.
Two drag minimization scenarios are performed,
which are unconstrained and constrained
optimization.
The
unconstrained
scenario
considers minimization drag only without any
constraint on other aerodynamic performance.
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First scenario is performed to see how much
minimization can be achieved from the original
airfoil. However, there is a possibility that the drag
coefficient can be pushed to as lower value as it
could get but it sacrifices other aerodynamic
performances. Second scenario includes lift
coefficient constrain on the mathematical
optimization model to see how drag can be
minimized by still keeping the value of original lift
coefficient. To deal with constrained problem, the
constrained optimization is transformed into
unconstrained one by introducing multiplicative
form penalty function to the objective function
(equation 8).
(8)
In sense of swarm intelligence, particle
that violates the solution would be penalized
hence it has lower chance to be the leader of the
swarm. Swarm would then have a tendency to not
following the move of penalized particle. In other
word, the optimization process is move away from
the infeasible area of search space.
The original airfoil is generated by 16
control points B-spline. Ordinary nonlinear leastsquares (nonlinear data-fitting) technique was
used to obtain the location of control points that
approximate original shape well. Fig. 9 shows the
geometry comparison between initial and created
airfoil, it can be seen that the geometry of created
airfoil can approximates well the shape of the
original one. The created S1223 has close
characteristic from the original S1223 at small
angle of attack but start to get differs on higher of
angle of attack (fig. 10).
Figure 10: Comparison of Cl vs α (left figure ) of original (solid
line) and created S1223 Airfoil (dashline) and Cd vs α (right
figure)
The airfoil is optimized on design condition
6
0
of Re = 0.2*10 , α = 2 , and M = 0.1, where this
condition is the same as in reference [9].
In all scenarios, PSO parameters were set to
the following value:




c1 = c2 = 1.4691
N = 20 (Amount of particles)
wi(t) reduce linearly from 0.9 to 0.4 from
the first to last iteration.
Maximum generation = 500
st
4.1
1
Scenario:
Unconstrained
minimization of S1223 airfoil
drag
Minimization of lift to drag ratio of S1223
airfoil was done without any constraint subject the
optimization
problem.
The
optimization
mathematical scenario is as follow:
Minimize Cd
(9)
The whole geometry of optimized airfoil
after 500 generation of PSO iteration is shown on
figure (11). It can be seen that there is a drastic
change between the geometry of original and
optimized one. While the original airfoil has a thick
shape profile, the optimized airfoil is a lot thinner
than the original airfoil. The geometry change is
also so large that the new airfoil doesn’t preserve
the geometrical characteristic of the original S1223
airfoil. While the leading edge part of optimized
airfoil seems only look thinner, the trailing edge
part is physically has a great difference compared
to the initial.
Figure 9: Geometry of original (solid line) and created (dashed
line) S1223 airfoil
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The 4th AUN/SEED-Net RC MeAe 2012
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drag coefficient area without any restriction. In
practice, airfoil with low value of drag coefficient
doesn’t ensure that it has also good performance
of lift coefficient. The second scenario includes this
type of constraint in order to find airfoil with lower
drag coefficient and reasonable value of lift
coefficient performance.
Figure 11: Original airfoil (blue solid line) and optimized airfoil
(red dashed line) on 1st scenario
Cl
Cd
Cl / Cd
S1223
1.4022
0.0188
74.78
S1223Opt1
0.9466
0.0104
74.58
Δ (%)
-32.5%
-44.6%
-0.26%
Table 2: Aerodynamic characteristic comparison between
original S1223 airfoil and optimized airfoil (1st scenario)
Because of the decreasing lift coefficient
value of new airfoil on the design condition, it is
already expected that the value of Cl,max is also
decreasing. This decrement can be seen clearly
on fig. 14. The new airfoil has lower drag in design
condition but higher drag in high angle of attack.
Nonetheless, the new airfoil from first scenario is
not recommended for practical use since the
decrement on lift coefficient is too significant.
Figure 12: Leading edge comparison between original airfoil
(blue solid line) and optimized airfoil (red dashed line) on 1st
scenario
Figure 13: Trailing edge comparison between original airfoil
(blue solid line) and optimized airfoil (red dashed line) on 1st
scenario
Reviewing
the
main
objective
of
minimizing the drag coefficient of initial airfoil, the
new airfoil can achieve significant decrement of
drag coefficient from the value of 0.0188 to 0.0104
(44.6%). However, the drawback is that the new
airfoil’s lift coefficient value on design condition
was decreased significantly from 1.4022 to 0.9466
(32.5%). This deterioration is undesired since the
high lift special characteristic of S1223 is lost on
the new airfoil.
Taking a conclusion from the first
optimization scenario, there is no guarantee that
the optimized airfoil would have overall good
aerodynamic performance if there is no constrain
added. Whole area in search space is a feasible
area so the solutions can move freely in search
space; it can discover the location of minimum
Figure 14: Comparison of Cl vs α (left figure) and Cd vs α (right
figure) of original (solid line) and optimized airfoil of 1st
scenario (dashline)
nd
4.2
2
Scenario:
Constrained
minimization of S1223 airfoil
drag
Based on the result of first scenario, it can
be concluded that the unconstrained minimization
of drag coefficient resulted in new airfoil that has
degraded value of lift coefficient. To ensure that
the lift coefficient doesn’t degrade while keeping
the goal of drag minimization, constraint in lift
coefficient need to be added; it is important to
keep the new lift coefficient near the original value.
Therefore, the added constrain is the optimized
airfoil value shouldn’t has lift coefficient lower than
the original one. Multiplicative form penalty
function with penalty term of 1.2 is employed to
penalize the solutions that enter the infeasible
area on hyperspace of decision variables. The
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The 4th AUN/SEED-Net RC MeAe 2012
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mathematical optimization problem then can be
stated as:
Minimize Cd*p(x)
Subject to Cl
(10)
1.4022 (Original Cl)
Where p(x) =
Result from PSO for constrained drag
minimization shows that the final airfoil after 300
iterations is the airfoil with geometry closely
resembles to the initial S1223 airfoil. It can be said
that the shape profile optimized airfoil still maintain
the geometrical characteristic of true S1223 airfoil.
Fig.16 depicts the geometry comparison between
two airfoils, where the optimized one has smaller
thickness profile compared to the initial airfoil. This
difference can be clearly seen on leading edge
zoomed up depiction on fig. 17. Trailing edge part
of optimized airfoil doesn’t have quite great
changes; still a geometry difference can be
noticed.
Figure 18: Leading edge comparison between original airfoil
(blue solid line) and optimized airfoil (red dashed line) on 2nd
scenario
Just like as it expected, the new airfoil can
kept the lift coefficient value near the initial value
with quite significant improvement in drag
coefficient. In fact, lift coefficient values of both
airfoils are the same. While the lift coefficient value
was successfully kept in the same value, quite
significant decrement of drag coefficient value from
0.0188 to 0.0128 (-31.68%) is achieved, resulting
in increasing lift to drag ratio value from 74.78 to
108.93 (45.67%) Even the drag coefficient from
first scenario is lower than the second scenario,
the overall performance of airfoil from second
scenario is more satisfying since it can find good
trade-off between lift and drag coefficient.
Cl
Cd
Cl / Cd
S1223
1.4022
0.0188
74.78
S1223Opt2
1.4022
0.0128
108.93
Δ (%)
0%
-31.36%
45.67%
Figure 16: Original airfoil (blue solid line) and optimized airfoil
(red dashed line) on 2nd scenario
Table 3: Aerodynamic characteristic comparison between
original S1223 airfoil and optimized airfoil (2st scenario)
Figure 17: Leading edge comparison between original airfoil
(blue solid line) and optimized airfoil (red dashed line) on 2nd
scenario
Comparison of Cl vs α and and Cd vs α of
original and optimized S1223 airfoil of second
scenario is shown on fig. 19. Even decrement of
drag minimization on design condition can be
achieved, trade-off occurred in decreasing value of
Cl,max and larger drag coefficient value in higher
angle of attack. Mathematical optimization model
and the optimization algorithm that don’t include
these values is the cause for this decrement of offdesign aerodynamic performance. To solve this
problem, multi-objective optimization algorithm that
considers off-design condition should be
developed.
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The 4th AUN/SEED-Net RC MeAe 2012
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References
Figure 19: Comparison of Cl vs α (left figure) and Cd vs α (right
figure) of original (solid line) and optimized airfoil of 2nd scenario
(dashline)
1. Conclusion
Drag minimization based on single objective
PSO which based on swarm intelligence is
presented on current paper. S1223 airfoil which
performs well for Low Reynolds number
application is considered as the target airfoil to
be optimized. The result shows that PSO works
well for aerodynamic optimization and has a
great potential to be continuously developed for
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Single objective PSO can find optimized airfoil
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Acknowledgment
This work is funded and supported by
ITB’s Program Riset dan Inovasi KK 2011. We
also want to express our gratitude to Arief
Hafizuddin for kindly helping us in PSO code
development.
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