Pada dasarnya saya adalah seorang ahli aerodinamika, jadi penelitian
saya dibidang aerodinamika.
Saya sudah membimbing banyak mahasiswa, baik S1 , S2 maupun S3.
Sebagian dari judul2 penelitian yang pernah saya berikan kepada
mahasiswa S1 adalah sbb:
Topic 1
Supervisor AProf. Hadi Winarto
Topic Title Propeller Aerodynamic Analysis and Design
Students needed 1 or 2
Abstract The student is required to analyze and design a propeller for
a R/C model aeroplane. RMIT Articles on BEMT and a software for
propeller analysis will be provided. Other articles can be found on
the internet and some of those internet resource addresses are given
below:
Propeller Design and Analysis
The operation of the propeller is analyzed by the use of the
distribution of forces along the radius, combined with theoretical
equations. The data were obtained in the NACA 20-foot wind tunnel on a
4-foot-diameter, two-blade propeller, operating in front of four body
shapes, ranging from a small shaft to support the propeller to
conventional NACA cowling. A method of estimating the axial and the
rotational energy in the wake as a fractional part of the propeller
power is given. A knowledge of the total thrust and torque is
necessary for the estimation.
An Adobe Acrobat (PDF) file of the entire NASA report:
UK: http://naca.central.cranfield.ac.uk/reports/1941/naca-report-712.pdf
US: http://naca.larc.nasa.gov/reports/1941/naca-report-712/
http://www.mh-aerotools.de/airfoils/index.htm
http://www.mh-aerotools.de/airfoils/pylonprops_2.htm
http://www.mh-aerotools.de/company/paper_1/epplerhepperle.htm
http://www.woodenpropeller.com/Basic_Propeller_Design.html
http://www.woodenpropeller.com/Blade_outline.html
http://www.woodenpropeller.com/Sopwith_Pup.html
http://www.woodenpropeller.com/blueprint.jpg
http://www.grc.nasa.gov/WWW/K-12/airplane/propanl.html
http://www.ace.gatech.edu/experiments2/6514/aircraft/fall02/propeller.htm
http://www.fluent.com/about/news/newsletters/03v12i2_fall/a2.htm
http://www.fluent.com/about/news/newsletters/03v12i2_fall/pdfs/nl6.pdf
http://www.eaa.org/benefits/sportaviation/S407-PropDesign_5.xls
http://www.jcpropellerdesign.com/
Topic 2
Supervisor AProf. Hadi Winarto
Topic Title Aerodynamic Analysis of 2-D Wing in Ground Effect using
Thin Airfoil Theory , Panel Method and Lifting Line Theory
Students needed 1 or 2
Abstract It is well known that as an aircraft approaches the surface
of the runway when landing, the coefficient of lift acting on the
aircraft increases considerably and the drag coefficient decreases
significantly. This effect is known as the wing in ground effect. The
considerably higher lift to drag ratio acting on a wing when close to
a surface means that an aircraft that flies close to the ground would
enjoy greater aerodynamic efficiency or lift to drag ratio, compared
to the one that flies very high up in the sky. This is the basic
principle behind the great interest in developing a winged boat, which
is referred to as a wig craft for transportation purposes. The wig
craft is much faster and more efficient than transport by a ship, and
cheaper to operate than an aircraft while capable of flying at half
the speed of an aircraft. An Australian company has received an order
to build such a wig craft (see the following web site)
http://www.australianhovercraft.com/
In this project the student is required to do an aerodynamic analysis
of the lift acting on a2-D wing as the distance between the wing and
the ground or surface is reduced to less than the chord of the wing.
Obviously in actual fact the wing of a wig craft is a 3-D shape and
should be analysed as such. However, the problem becomes too difficult
for an undergraduate thesis. It is with that constraint in mind that
the problem is simplified to a 2-D problem. The presence of the ground
is simulated by using the mirror image technique. The student(s) will
be required to write computer programs and will be guided in
developing the necessary theoretical backgrounds.
Some information on wig crafts can be obtained from the following web
site http://www.se-technology.com/wig/index.php
Topic 3
Supervisor AProf. Hadi Winarto
Topic Title Application of Conformal Mapping in the Analysis of Aerofoils
Students needed 1
Abstract By applying the incompressible and inviscid flow assumptions,
the very complicated Navier Stokes equations can be simplified to
become the Laplace Equation. This is a linear second order partial
differential equation that can be solved quite easily using the theory
of complex variables. The solution for a fluid flow around a circle
can be obtained almost immediately, and then by using the concepts of
conformal mapping the solution for the flow around a circle can be
obtained. The simplest type of conformal mapping is the Joukowski
transformation, which can be generalized by using the Karman-Trefftz
transformation. A more difficult problem is to specify the shape of
the aerofoil and then we have to evaluate the transformation function.
A method to do this is by means of the Laurent Series transformation.
In this project the student is required to develop computer programs
based on Joukowski and Karman-Trefftz transformations to analyse the
aerodynamic properties of Joukovski and Karman-Trefftz aerofoils. The
results of the analysis are then validated by comparison with the
analysis results using XFOIL, FLUENT or other well proven softwares.
Guidance will be provided in the development of the theoretical
foundation of the softwares to be developed.
Topic 4
Supervisor AProf. Hadi Winarto
Topic Title Numerical solution of the Falkner Skan Boundary Layer Equation
Students needed 1
Abstract The Falkner Skan Equation is the governing equation for the
laminar boundary layer flow over a wedge and is given as follows
where is a constant
The boundary conditions are
The student is required to develop a computer software based on MATLAB
to solve the above equation using a suitable numerical method
Topic 5
Supervisor AProf. Hadi Winarto
Topic Title Solution of the Blasisus boundary layer equation using
several numerical methods
Students needed 1
Abstract The Blasius equation is the governing equation for the
laminar boundary layer flow over a flat plate. It may also be
considered as a special case for the Falkner Skan where the wedge
angle is zero or when the value of the constant in the Falkner Skan
equation is zero.
In this project the student is required to compare a number of
numerical methods that are suitable for solving the following Blasius
equation.
The boundary conditions are
Topic 6
Supervisor AProf. Hadi Winarto
Topic Title Solution of the boundary layer flow over the surface of an
arbitrary aerofoil using the method of Thwaites and the integral
boundary layer equation
Students needed 1 or 2
Abstract A short and simplified description of the Thwaites method can
be read on the following web site. Further information can be obtained
from most textbooks on Fluid Mechanics
http://www.aeronautics.hut.fi/edu/kurssit/130/Luento_04.pdf
The very complicated partial differential equations governing the
boundary layer flow along a surface with arbitrary smoothly varying
pressure distribution can be simplified by taking their integrals.
This converts the partial differential equations into a single
ordinary differential equation (ODE) that is much easier to solve.
However, the ODE contains 2 unknown parameters and thus can't be
solved unless 2 extra equations can be derived. These 2 equations are
empirical in nature and Thwaites method involves certain assumptions
about those 2 extra empirical equations.
The student is required to develop a software for solving the integral
momentum equation based on Thwaites method. The software must then be
combined with the panel method developed by other students (and will
be made available) so that we will have an analysis software for a low
speed viscous arbitrary airfoil. The inviscid solution obtained using
the panel method or conformal mapping can then be corrected for
viscous effect using the integral momentum solution.
Topic 7
Supervisor AProf. Hadi Winarto
Topic Title Application of Milne-Thompson Circle Theorem to
investigate the flow around 2 or more cylinders
Students needed 1
Abstract In a heat exchanger there is a large number of parallel
cylinders. Similarly the risers for an oil rig platform may be
modelled as a number of parallel cylinders. The solution for the
problem of flow around circular cylinders can be obtained by means of
the Milne-Thompson circle theorem in the theory of complex variable,
as follows:
Let there be irrotational 2-D flow of incompressible inviscid fluid in
the z-plane. Let there be no rigid boundaries, and let the complex
potential of the flow be f(z), where the singularities of f(z) are all
at a distance greater than a from the origin. If a circular cylinder
typified by its cross section the circle C, , be introduced into the
field of flow, the complex potential becomes .
A uniform flow in the x-y plane flowing horizontally from left to
right is represented by its complex potential as , where the complex
variable z is defined as z = x +i y. The complex potential function is
composed by its 2 components, namely the potential function, (x,y)
and the stream function , as follows . Thus the stream function for
the uniform flow is simply and the streamlines are simply the
horizontal lines y = constant for different values of the constant.
If now a circle of radius a is inserted into the flow, the Milne
Tompson circle theorem gives us the expression for the complex
potential function for the flow around a circle in a uniform
horizontal flow as follows:
Therefore and
The stream function for the flow is thus given by the expression or
. Note that if the constant has a vale of zero then we have , which is
the equation for the circle C and thus C is a streamline. Other
streamlines can be obtained by varying the value of the constant .
If another circle is now inserted into the flow, the equation for the
potential function for the flow around 2 circles can be found.
However, the solution is quite complicated and must be done
numerically and involves an iterative method.
The student is expected to write a computer program for solving the
problem of flow around at least 2 circles using the above theorem.
Topic 8
Supervisor AProf. Hadi Winarto
Topic Title Application of Conformal mapping for the generation of
structured computational mesh around an aerofoil shape.
Students needed 1 or more
Abstract Softwares based on the Euler or Navier Stokes equations
require computational mesh to be generated around the shape of the
aerofoil whose properties are to be computed. All CFD flow solvers are
supplied with a computational mesh generation software such that the
user doesn't have to worry about having to prepare the needed mesh
from first principle, which is a very difficult and tedious task.
However, if the user has no idea whatsoever about the process of
generating the mesh, then it is likely that the mesh generation
software is not applied properly and this will lead to computational
errors.
In this project the student is required to develop a computer program
for generating a structured orthogonal mesh around any given aerofoil
shape. Initially the orthogonal computing mesh is prepared around a
circle, and then the circle is transformed into the given aerofoil
shape. The mesh around the circle is then also transformed using the
same transformation rule of conformal mapping to give an orthogonal
mesh around the aerofoil. Basically there are 3 types of mesh, namely
O, H and C types and all 3 need to be investigated.
The transformation to be applied is limited to theKarman-Trefftz or
Joukovski transformation.
Topic 9
Supervisor AProf. Hadi Winarto
Topic Title Aerofoil analysis using first and second order Vortex
Panel Methods with Neumann Boundary conditions
Students needed 1 or 2
Abstract The aerodynamic properties of an aerofoil can be analysed
using the vortex panel method. A thesis based on vortex panel method
with Dirichlet boundary condition has been done by 2 students of RMIT
in the past. This is a similar topic but the boundary condition is
changed to the Neumann boundary condition.
The student is required to develop a computer program that can be used
to analyse the aerodynamic properties of a single aerofoil at various
angle of attacks.
Topic 10
Supervisor AProf. Hadi Winarto
Topic Title High lift devices analysis using Vortex Panel Methods with
Neumann Boundary conditions
Students needed 1 or 2
Abstract This is similar to topic number 54, but it involves an
aerofoil with 2 or more components to be analysed. On take off, an
aircraft requires a much higher value of lift coefficient compared
to when it is cruising. This can be achieved by extending the flap at
the trailing edge of the wing, which of course consists of at least 2
components, namely the main wing plus the flap. On a modern aircraft
the flap is usually quite complex and may consist of 2 or more
distinct parts.
The student is required to develop a computer program, which is a
further development of topic 54.
Topic 11
Supervisor AProf. Hadi Winarto
Topic Title High lift devices analysis using Vortex Panel Methods with
Dirichlet Boundary conditions
Students needed 1 or 2
Abstract This is similar to topic 55, except that the boundary
condition to be applied is the Dirichlet boundary condition rather
than the Neuman BC.
Topic 12
Supervisor AProf. Hadi Winarto
Topic Title The aerodynamic implications of a morphing wing
Students needed 1 or more
Abstract With the development of smart materials such as SMP(shape
memory polymers) and SMA (shape memory alloys) etc it is now almost
possible to develop an aircraft or UAV that can change its shape in
flight, depending on the aerodynamic performance required at that
stage of flight.
In this thesis the student is required to collect information on smart
materials and wing morphing in general, and then offer some analysis
on how the new technologies can be applied in the design of a UAV or
an aircraft that has superior aerodynamic performance than existing
aircrafts. Some computation of aerofoil properties will be required in
this project, using existing softwares such as XFOIL, JAVAFOIL or
FLUENT etc. A lot of original thinking is required in this project,
which should be much more than just a literature review on the topic.
Topic 13
Supervisor AProf. Hadi Winarto
Topic Title The aerodynamic implications of the requirement for a
stealthy aircraft
Students needed 1 or more
Abstract Future or generation 5 fighter aircraft such as the F22
Raptor or F35 JSF is distinguished from previous generation fighters
by the requirement, among other things, that the aircraft must be
stealthy. This means that the outer geometry of the aircraft must be
composed of "discontinuous" surfaces intersecting at a small angle
with each other, such that radar or other electromagnetic waves
incident on any surface will not be reflected back to the waves
emitter and detector. Fuel tanks and armament stores must also be
located inside the outer surface of the aircraft because external
pylons and weapons etc are very good radar reflectors. These
requirements obviously must have quite an impact on the aerodynamics
of the aircraft, which traditionally has a nice smooth curving
aerodynamic shape. On the other hand the performance of the fighter
must be at least equal to, if not better than, the previous generation
aircrafts.
The student is required to investigate how to determine the outer
shape of the generation 5 fighters such that the requirements of being
stealthty but at the same time having a good aerodynamic performance,
can be achieved satisfactorily.
Topic 14
Supervisor AProf. Hadi Winarto
Topic Title Pitching or Longitudinal Stability of a BWB aircraft
Students needed 1 or more
Abstract Recently Boeing released the following statement:
HAMPTON, Va., May 04, 2006 -- In cooperation with NASA and the U.S.
Air Force Research Laboratory, the Phantom Works organization of
Boeing [NYSE: BA] is taking another step toward exploring and
validating the structural, aerodynamic and operational advantages of a
futuristic aircraft design called the blended wing body, or BWB.
Furthermore it is claimed by Boeing and NASA that the BWB concept can
be up to 30percent more fuel efficient than a comparable conventional
wing and tube concept aircraft. However, due to the fact that BWB
aircraft doesn't have a tail, it does have a problem with its
longitudinal stability.
In this project the student is required to do a thorough literature
review on the topic of Blended Wing Body aircraft. Furthermore the
student should provide an insightful analysis on the performance
and/or the longitudinal stability of the BWB aircraft. The student
should try to answer the question of whether the BWB concept is really
viable and that it is realistic (or otherwise) for Boeing to suggest
that BWB aircraft is the new shape of the 21st century, and that a BWB
aircraft with 800 passengers is really the competitive answer to
Airbus A380 super jumbo. Further information on BWB aircraft can be
obtained from the internet or other sources. Some of the internet
resources are given below
http://www.nasa.gov/centers/langley/news/factsheets/FS-2003-11-81-LaRC.html
http://oea.larc.nasa.gov/PAIS/pdf/FS-1997-07-24-LaRC.pdf
http://www.nasa.gov/vision/earth/improvingflight/blended_wing.html
http://www.af.mil/news/story.asp?id=123021728
http://www.boeing.com/news/releases/2006/q2/060504b_nr.html
http://www.boeing.com/phantom/news/2006/q2/060504b_nr.html
http://www.twitt.org/bldwing.htm
http://www.promotex.ca/articles/cawthon/2006/2006-05-15_article.html
http://www.afrl.af.mil/articles/061906_BWBConcept.asp
http://www.newscientisttech.com/article/dn8310.html
PhD thesis with the topic of: FLYING AND HANDLING QUALITIES OF A
FLY-BY-WIRE BLENDED-WING-BODY CIVIL TRANSPORT AIRCRAFT
http://www.xs4all.nl/~miezor/BWBPage.htm
Topic 18
Supervisor AProf Hadi Winarto and Dr Javid Bayandor
Topic Title Aerodynamic Modelling of Flapping Wings
Students needed More than 1
Abstract Nature's solution for flight is flapping wings. Man made
machines can fly faster and higher using fixed (aircraft) and rotary
(helicopter) wings.
However, for small scale machines it is believed that flapping wings
are better solutions than fixed or rotary wings. In this project the
student will investigate the kinematics of insect or bird's flapping
wings and how lift is generated. A more detailed investigation should
then be conducted to numerically study 2-D equivalence of a flapping
wing namely pitching or oscillating airfoils. Another aspect of a
flapping wing that should be studied in 2-D simulation is heaving
airfoils. A more complete 2-D simulation of a flapping wing should
then involve both heaving and pitching motions. These are unsteady
aerodynamics, which are quite distinct from the steady aerodynamics of
a translating fixed wing or a rotating wing.
Topic 19
Supervisor AProf Hadi Winarto
Topic Title Numerical Solution of Taylor-MacColl Conical Supersonic Flow
Students needed 1
Abstract Compressible aerodynamics is very distinct from
incompressible aerodynamics in that the fluid density is a variable.
In compressible aerodynamics a flow discontinuity called shock wave
may exist, across which flow properties change very abruptly. In this
numerical study the student is required to create a computer program
to solve first the simpler 2-D oblique shock wave problem, and then
the similar but more difficult problem of a supersonic flow about an
axisymmetric cone. The governing equation for this flow is the
Taylor-MacColl differential equation, which can only be solved
numerically.
The student should develop a computer program that can solve both the
2-D oblique shock wave and the conical flow problems.
Topic 20
Supervisor AProf Hadi Winarto
Topic Title Design and Analysis of Supersonic Nozzle Using the Method
of Characteristics
Students needed 1
Abstract In a subsonic wind tunnel the test section flow velocity can
be varied continuously by varying the ratio of the pressure within the
settling chamber and the pressure at the test section. This is not
true for a supersonic wind tunnel, where the test section flow speed
or Mach number is determined by the area ratio of the test section to
the nozzle throat, provided that the pressure ratio is sufficiently
large. Furthermore, the shape of the nozzle is critical in determining
whether a shock wave is formed within the nozzle or not. To get a good
flow quality within the test section or nozzle exit, the flow must be
isentropic without any discontinuity anywhere within the tunnel, thus
the nozzle should be designed to be shock free. The method of
characteristics (MOC) is quite easy to understand and the student
shoud develop a computer program basedon MOC to design the shape of a
supersonic nozzle for any desired Mach number at the test section.
Topic 21
Supervisor AProf Hadi Winarto
Topic Title Aerodynamic Study of the BWB Configuration for the Next
Generation of Supersonic Transport Aircraft
Students needed More than 1
Abstract Last June the French and Japanese Aerospace Industry
Organisations signed an agreement to jointly develop a supersonic
transport aircraft (SST) to replace the retired Concorde. It is likely
that the next generation SST would be a BWB (Blended Wing Body)
configuration, which can carry 300+ passengers and cruising at a Mach
number of greater than 1.8. In this project, the student(s) should
carry out a thorough literature survey of works that have been carried
out regarding the Supersonic BWB. In particular the student should
make personal contribution in the form of some detailed analysis of
the aerodynamic, performance and the stability and control of a BWB
aircraft, as compared to the more traditional aircraft configuration.
salam
HW
--- In stt-adisutjipto@yahoogroups.com, agus supriono
wrote:
>
> Ass.Wr.Wb.
> Salam pak Ardi, Gimana keadaan dan kabar pak ardi sehat-sehat
ajakan, pak saya mau tanya anak STTA yang dibimbing pak hadinanto
siapa, pak ardi punya tentang hasil-hasil penelitian-penelitian beliau
tentang apa saja pak, pak ardi punya softcopy untuk Matlab dan
petunjuk-petunjuknya.Terima kasih Pak sebelumnya.
> Wass.Wr.Wb.
>
http://groups.yahoo.com/group/stt-adisutjipto/message/502
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