project report ansys workbench - nithin l devasia
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Project Report on Ansys FLUENT AND STRUCTURAL ANALYSIS OF NACA 4515 AEROFOIL
NITHIN L DEVASIA
Submitted By:
CADD Centre Thiruvananthapuram | Ansys Workbench | 1
VANROSS Jn.
THIRUVANANTHAPURAM
Certificate
This is to certify that this project report entitled
“FLUENT AND STRUCTURAL ANALYSIS OF NACA 4515
AEROFOIL” is a complete record of the work done by
NITHIN L DEVASIA for the requirement of the award of
course on MASTER DIPLOMA IN PRODUCT DESIGN
AND ANALYSIS during the year 2014 from CADD
CENTRE, VANROSS Jn. THIRUVANANTHAPURAM.
Mr. RAHUL KRISHNAN
Senior CADD Engineer
CADD CENTRE
Vanross Jn.
Mr. TINU V G
Technical Leader
CADD CENTRE
Vanross Jn.
Guided by: Verified by:
CADD Centre Thiruvananthapuram | Ansys Workbench | 2
ACKNOWLEDGEMENT
I also want to thank the CADD Centre Thiruvananthapuram, for giving me
quality training in Ansys Workbench and providing me the opportunity and
facilities to pursue this project and present the report.
I take this opportunity to express my deep sense of gratitude to my
concerned faculty, Mr. Rahul Krishnan – Senior CADD Engineer of
CADD Centre, Vanross Junction, Thiruvananthapuram for his valuable
suggestions and guidance, especially for the technical information imparted by him
in both theory and practical session.
I also use this opportunity to express my heartfelt thanks to
Mr. TINU V G, Technical Leader of CADD Centre, for the encouragement
provided by him throughout my course.
I appreciate the team who made the efforts to create the CADD Centre
course material in such a simple and effective manner. It really motivated me to
explore more on the software further.
Last but not the least, I accord myself the privilege of thanking all other
members of CADD Centre who were directly and indirectly connected to this
project.
Nithin L Devasia
CADD Centre Thiruvananthapuram | Ansys Workbench | 3
Table of Contents PREFACE ............................................................................................................................................. 4
ABOUT CAE .................................................................................................................................... 5
ANSYS and its CAPABILITIES ...................................................................................................... 8
ABOUT THE PROJECT .................................................................................................................... 14
SCOPE OF THE PROJECT and PROBLEM DEFININTION ........................................................ 20
APPROACH AND PROCEDURE ..................................................................................................... 21
INFERENCE....................................................................................................................................... 60
SUGGESTIONS AND CONCLUSIONS........................................................................................... 61
REFERENCE ...................................................................................................................................... 62
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PREFACE
Nowadays we are depending more on computers due to their speed in data
processing, visualization capabilities, data storing in documentation as well as
numerical calculations etc. They have become an integral part of everyone’s daily
life. They find applications in communication, entertainment, accounting, and
scientific research and in production industries.
In production industries, computers are used from designing, controlling
manufacturing operations, etc., increasing efficiency and productivity. This
particular field of application being called Precise Engineering Cycle is further
classified into Computer Aided Designing (CAD), Computer Aided Engineering
(CAE) and Computer Aided Manufacturing (CAM).
The product designers are posted with challenge to bring out products that
could exceed the expectations of the consumer consistently in product quality, price
and performance. Design engineers are constantly working on these challenges in
order to enhance the product quality and performance while reducing cost.
Computer Aided Engineering (CAE) tools assists design engineers in achieving the
challenges posted to them time to time. There are of many application packages
which all particularly strong in specific areas of CAE. But there are also ones that
have good all-round capabilities like ANSYS, Altair HyperWorks, Abaqus, ADINA
etc.
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ABOUT CAE
Computer aided engineering (CAE) refers to a collection of software and hardware
tools integrated into a system (computer) that is providing the circuit designer and
circuit troubleshooter with step-by-step assistance during each phase of the design
and analysis cycle, as well as during development, documentation, and
maintenance. Under the CAE umbrella a number of commonly called "automated
design tools," which are the software components of CAE, are revolutionizing and
transforming engineering environments from the "hands-on' way of conducting
business into a virtual or simulated "hands-on" mode of operating; and are having a
tremendous impact throughout all engineering disciplines. They have not yet
displaced bread boarding and other methods of developing circuit boards yet but
are making their presence known to the point of being totally necessary in the
design of certain devices. It is the intention of this report to promote the use of
these tools in the government by providing engineering management with an
overview of the hardware and software products available for electronic
simulation, while covering trends, new technologies, and costs.
CAE is also defined very broadly as ―The computer tools used to assist in
engineering design, development and optimization tasks. ―Models of systems may
be separated into static or dynamic systems, each having a particular purpose.
Static models are independent of time. Dynamic models are time varying.
Software tools that have been developed to support these activities are considered
CAE tools. CAE tools are being used, for example, to analyze the robustness and
performance of components and assemblies. The term encompasses simulation,
validation, and optimization of products and manufacturing tools. In the future,
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CAE systems will be major providers of information to help support design teams
in decision making. In regard to information networks, CAE systems are
individually considered a single node on a total information network and each node
may interact with other nodes on the network. CAE systems can provide support to
businesses. This is achieved by the use of reference architectures and their ability
to place information views on the business process. Reference architecture is the
basis from which information model, especially product and manufacturing
models. The term CAE has also been used by some in the past to describe the use
of computer technology within engineering in a broader sense than just engineering
analysis. It was in this context that the term was coined by Jason Lemon, founder
of SDRC in the late 1970s. This definition is however better known today by the
terms CAx and PLM.
CAE areas covered include:
Stress analysis on components and assemblies using FEA (Finite Element
Analysis).
Thermal and fluid flow analysis Computational fluid dynamics (CFD).
Multibody dynamics (MBD) & Kinematics.
Analysis tools for process simulation for operations such as casting,
molding, and die press forming.
Optimization of the product or process.
Safety analysis of postulate loss-of-coolant accident in nuclear reactor using
realistic thermal-hydraulics code.
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In general, there are three phases in any computer-aided engineering task:
Pre-processing – defining the model and environmental factors to be applied
to it. (typically a finite element model, but facet, voxel and thin sheet
methods are also used)
Analysis solver (usually performed on high powered computers)
Post-processing of results (using visualization tools)
This cycle is iterated, often many times, either manually or with the use of
commercial optimization software.
CAE tools are very widely used in the automotive industry. In fact, their use has
enabled the automakers to reduce product development cost and time while
improving the safety, comfort, and durability of the vehicles they produce. The
predictive capability of CAE tools has progressed to the point where much of the
design verification is now done using computer simulations rather than physical
prototype testing.
CAE dependability is based upon all proper assumptions as inputs and must
identify critical inputs. Even though there have been many advances in CAE, and it
is widely used in the engineering field, physical testing is still used as a final
confirmation for subsystems due to the fact that CAE cannot predict all variables in
complex assemblies (i.e. metal stretch, thinning).
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NSYS and its CAPABILITIES
.
Drafting & Design
Design for assembly
Computer aided
manufacture
Modeling & Analysis Dynamic analysis
Rapid control
prototyping
Finite element
analysis
Mechanism design
Discrete event
simulation
Manufacture
Computer aided part
programming (CNC)
Distributed numerical
control
Coordinate measuring
Flexible
assembly/manufacturin
g systems
Production Planning
& Control Scheduling Quality
control
Materials
requirements
planning
Just-in-time
manufacturing
Computer
Aided
Engineering
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ANSYS and its CAPABILITIES
ANSYS Workbench is the framework upon which the industry’s broadest suite of
advanced engineering simulation technology is built. An innovative project
schematic view ties together the entire simulation process, guiding the user every
step of the way. Even complex multiphysics analyses can be performed with drag-
and-drop simplicity. With bi-directional CAD connectivity, an automated project
update mechanism, pervasive parameter management and integrated optimization
tools, the ANSYS Workbench platform delivers unprecedented productivity that
truly enables Simulation Driven Product Development.
The ANSYS Workbench framework hosts the following software products and
components:
COMMON TOOLS AND CAPABILITIES
• ANSYS CAD connections
• ANSYS Design Modeler
• ANSYS Meshing
• ANSYS DesignXplorer
• FE Modeler
FLUID DYNAMICS
• ANSYS CFX
• ANSYS FLUENT
• ANSYS Icepak
• ANSYS POLYFLOW
ANSYS Multiphysics
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STRUCTURAL MECHANICS
• ANSYS Mechanical
• ANSYS Structural
• ANSYS Professional
EXPLICIT DYNAMICS
• ANSYS Explicit STR
• ANSYS AUTODYN
• ANSYS LS-DYNA (setup-only in ANSYS Workbench)
ELECTROMAGNETICS
• ANSYS Emag
TURBO SYSTEM
• ANSYS BladeModeler
• ANSYS TurboGrid
• ANSYS Vista TF
OFFSHORE
• ANSYS AQWA
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ANSYS Workbench Features
Bidirectional, parametric links with all major CAD systems
Integrated, analysis-focused geometry modeling, repair, and
simplification via ANSYS DesignModeler
Highly-automated, physics-aware meshing
Automatic contact detection
Unequalled depth of capabilities within individual physics disciplines
Unparalleled breadth of simulation technologies
Complete analysis systems that guide the user start-to-finish through an
analysis
Comprehensive multiphysics simulation with drag-and-drop ease of use
Flexible components enable tools to be deployed to best suit engineering
intent
Innovative project schematic view allows engineering intent, data
relationships, and the state of the project to be comprehended at a glance
Complex project schematics can be saved for re-use
Pervasive, project-level parameter management across all physics
Automated what-if analyses with integrated design point capability
Adaptive architecture with scripting and journaling capabilities and API’s
enabling rapid integration of new and third-party solutions
Drag-and-Drop Multiphysics
The ANSYS Workbench platform has been engineered for scalability. Building
complex, coupled analyses involving multiple physics is as easy as dragging in a
follow-on analysis system and dropping it onto the source analysis. Required data
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transfer connections are formed automatically. As an example, consider the one-
way fluid structure interaction (FSI) simulation shown schematically below.
Drag-and-drop multiphysics: forming a link in the project schematic (at left) achieves data
transfer between the different physics, and creates imported loads in the downstream
simulation (shown inside the ANSYS Mechanical application at right).
The ANSYS Workbench platform automatically forms a connection to share the
geometry for both the fluid and structural analyses, minimizing data storage and
making it easy to study the effects of geometry changes on both analyses. In
addition, a connection is formed to automatically transfer pressure loads from the
fluid analysis to the structural analysis.
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Flexible Project Construction
Complete analysis systems are convenient because they contain all of the necessary
tasks or components to complete start-to-finish simulations for a wide variety of
physics. The project schematic has also been designed to be very flexible. You can
connect component systems—task-oriented, ―building block‖ systems—in a wide
variety of ways to suit your analysis needs.
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ABOUT THE PROJECT
An airfoil (in American English) or aerofoil (in British English) is the shape of a
wing or blade (of a propeller, rotor, or turbine) or sail as seen in cross-section.
An airfoil-shaped body moved through a fluid produces an aerodynamic force. The
component of this force perpendicular to the direction of motion is called lift. The
component parallel to the direction of motion is called drag. Subsonic flight airfoils
have a characteristic shape with a rounded leading edge, followed by a sharp
trailing edge, often with asymmetric curvature of upper and lower surfaces. Foils
of similar function designed with water as the working fluid are called hydrofoils.
The lift on an airfoil is primarily the result of its angle of attack and shape. When
oriented at a suitable angle, the airfoil deflects the oncoming air, resulting in a
force on the airfoil in the direction opposite to the deflection. This force is known
as aerodynamic force and can be resolved into two components: lift and drag. Most
foil shapes require a positive angle of attack to generate lift, but cambered airfoils
can generate lift at zero angle of attack. This "turning" of the air in the vicinity of
the airfoil creates curved streamlines which results in lower pressure on one side
and higher pressure on the other. This pressure difference is accompanied by a
velocity difference, via Bernoulli's principle, so the resulting flow field about the
airfoil has a higher average velocity on the upper surface than on the lower surface.
The lift force can be related directly to the average top/bottom velocity difference
without computing the pressure by using the concept of circulation and the Kutta-
Joukowski theorem.
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Examples of airfoils in nature and within various vehicles. Though not strictly an airfoil, the
dolphin flipper obeys the same principles in a different fluid medium.
A fixed-wing aircraft's wings, horizontal, and vertical stabilizers are built with
airfoil-shaped cross sections, as are helicopter rotor blades. Airfoils are also found
in propellers, fans, compressors and turbines. Sails are also airfoils, and the
underwater surfaces of sailboats, such as the centerboard and keel, are similar in
cross-section and operate on the same principles as airfoils. Swimming and flying
creatures and even many plants and sessile organisms employ airfoils/hydrofoils:
common examples being bird wings, the bodies of fish, and the shape of sand
dollars. An airfoil-shaped wing can create down force on an automobile or other
motor vehicle, improving traction.
Any object with an angle of attack in a moving fluid, such as a flat plate, a
building, or the deck of a bridge, will generate an aerodynamic force (called lift)
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perpendicular to the flow. Airfoils are more efficient lifting shapes, able to
generate more lift (up to a point), and to generate lift with less drag.
A lift and drag curve obtained in wind tunnel testing is shown on the right. The
curve represents an airfoil with a positive camber so some lift is produced at zero
angle of attack. With increased angle of attack, lift increases in a roughly linear
relation, called the slope of the lift curve. At about 18 degrees this airfoil stalls, and
lift falls off quickly beyond that. The drop in lift can be explained by the action of
the upper-surface boundary layer, which separates and greatly thickens over the
upper surface at and past the stall angle. The thickened boundary layer's
displacement thickness changes the airfoil's effective shape in particular it reduces
its effective camber, which modifies the overall flow field so as to reduce the
circulation and the lift. The thicker boundary layer also causes a large increase in
pressure drag, so that the overall drag increases sharply near and past the stall
point.
Airfoil design is a major facet of aerodynamics. Various airfoils serve different
flight regimes. Asymmetric airfoils can generate lift at zero angle of attack, while a
symmetric airfoil may better suit frequent inverted flight as in an aerobatic
airplane. In the region of the ailerons and near a wingtip a symmetric airfoil can be
used to increase the range of angles of attack to avoid spin–stall. Thus a large
range of angles can be used without boundary layer separation. Subsonic airfoils
have a round leading edge, which is naturally insensitive to the angle of attack. The
cross section is not strictly circular, however: the radius of curvature is increased
before the wing achieves maximum thickness to minimize the chance of boundary
layer separation. This elongates the wing and moves the point of maximum
thickness back from the leading edge.
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Supersonic airfoils are much more angular in shape and can have a very sharp
leading edge, which is very sensitive to angle of attack. A supercritical airfoil has
its maximum thickness close to the leading edge to have a lot of length to slowly
shock the supersonic flow back to subsonic speeds. Generally such transonic
airfoils and also the supersonic airfoils have a low camber to reduce drag
divergence. Modern aircraft wings may have different airfoil sections along the
wing span, each one optimized for the conditions in each section of the wing.
Movable high-lift devices, flaps and sometimes slats, are fitted to airfoils on almost
every aircraft. A trailing edge flap acts similarly to an aileron; however, it, as
opposed to an aileron, can be retracted partially into the wing if not used.
A laminar flow wing has a maximum thickness in the middle camber line.
Analyzing the Navier–Stokes equations in the linear regime shows that a negative
pressure gradient along the flow has the same effect as reducing the speed. So with
the maximum camber in the middle, maintaining a laminar flow over a larger
percentage of the wing at a higher cruising speed is possible. However, with rain or
insects on the wing, or for jetliner speeds, this does not work. Since such a wing
stalls more easily, this airfoil is not used on wingtips (spin-stall again).
Schemes have been devised to define airfoils – an example is the NACA system.
Various airfoil generation systems are also used. An example of a general purpose
airfoil that finds wide application, and predates the NACA system, is the Clark-Y.
Today, airfoils can be designed for specific functions using inverse design
programs such as PROFOIL, XFOIL and Aerofoil. XFOIL is an online program
created by Mark Drela that will design and analyze subsonic isolated airfoils.
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FLUENT AND STRUCTURAL ANALYSIS OF NACA 4515
AEROFOIL
The NACA airfoils are airfoil shapes for aircraft wings developed by the National
Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is
described using a series of digits following the word "NACA". The parameters in
the numerical code can be entered into equations to precisely generate the cross-
section of the airfoil and calculate its properties.
The NACA four-digit wing sections define the profile by:
1. First digit describing maximum camber as percentage of the chord.
2. Second digit describing the distance of maximum camber from the airfoil
leading edge in tens of percent of the chord.
3. Last two digits describing maximum thickness of the airfoil as percent of the
chord.
For example, the NACA 2412 airfoil has a maximum camber of 2% located 40%
(0.4 chords) from the leading edge with a maximum thickness of 12% of the chord.
Four-digit series airfoils by default have maximum thickness at 30% of the chord
(0.3 chords) from the leading edge.
The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber.
The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15%
as thick as it is long.
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AIRFOIL TERMINOLOGY
AIRFOIL NOMENCLATURE
The various terms related to airfoils are defined below:
The suction surface (a.k.a. upper surface) is generally associated with higher
velocity and lower static pressure.
The pressure surface (a.k.a. lower surface) has a comparatively higher static
pressure than the suction surface. The pressure gradient between these two
surfaces contributes to the lift force generated for a given airfoil.
The geometry of the airfoil is described with a variety of terms:
The leading edge is the point at the front of the airfoil that has maximum
curvature (minimum radius).
The trailing edge is defined similarly as the point of maximum curvature at
the rear of the airfoil.
The chord line is the straight line connecting leading and trailing edges. The
chord length, or simply chord , is the length of the chord line. That is the
reference dimension of the airfoil section.
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SCOPE OF THE PROJECT and PROBLEM DEFININTION
The Scope of this project is to design a 4515 aerofoil to work under extreme
conditions without undergoing failure. To prove this, we need to analyze the
aerofoil under a defined inlet velocity of 138 m/s in ANSYS FLUENT and a
structural analysis is carried out to find whether it is structurally stable under the
extreme conditions using ANSYS STRUCTURAL ANALYSIS. If the values
obtained from analysis is safe hence the design can be used for practical
application.
In this project, I am going to analyze fluid (air) flow over the NACA 4515 Aerofoil
and its Structural Analysis.
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APPROACH AND PROCEDURE
MODELING
The coordinate text file is imported in the design modeler and 3D curve is
generated using the coordinates given below
Group Point X_cord Y-cord Z-cord
1 1 1.00000 0.00000 0
1 2 0.99893 0.00039 0
1 3 0.99572 0.00156 0
1 4 0.99039 0.00349 0
1 5 0.98296 0.00610 0
1 6 0.97347 0.00932 0
1 7 0.96194 0.01303 0
1 8 0.94844 0.01716 0
1 9 0.93301 0.02166 0
1 10 0.91573 0.02652 0
1 11 0.89668 0.03171 0
1 12 0.87592 0.03717 0
1 13 0.85355 0.04283 0
1 14 0.82967 0.04863 0
1 15 0.80438 0.05453 0
1 16 0.77779 0.06048 0
1 17 0.75000 0.06642 0
1 18 0.72114 0.07227 0
1 19 0.69134 0.07795 0
1 20 0.66072 0.08341 0
1 21 0.62941 0.08858 0
1 22 0.59755 0.09341 0
1 23 0.56526 0.09785 0
1 24 0.53270 0.10185 0
1 25 0.50000 0.10538 0
1 26 0.46730 0.10837 0
1 27 0.43474 0.11076 0
1 28 0.40245 0.11248 0
1 29 0.37059 0.11345 0
1 30 0.33928 0.11361 0
1 31 0.30866 0.11294 0
1 32 0.27886 0.11141 0
1 33 0.25000 0.10903 0
1 34 0.22221 0.10584 0
1 35 0.19562 0.10190 0
1 36 0.17033 0.09726 0
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1 37 0.14645 0.09195 0
1 38 0.12408 0.08607 0
1 39 0.10332 0.07970 0
1 40 0.08427 0.07283 0
1 41 0.06699 0.06541 0
1 42 0.05156 0.05753 0
1 43 0.03806 0.04937 0
1 44 0.02653 0.04118 0
1 45 0.01704 0.03303 0
1 46 0.00961 0.02489 0
1 47 0.00428 0.01654 0
1 49 0.00107 0.00825 0
1 50 0.00000 0.00075 0
1 51 0.00107 -0.00566 0
1 52 0.00428 -0.01102 0
1 53 0.00961 -0.01590 0
1 54 0.01704 -0.02061 0
1 55 0.02653 -0.02502 0
1 56 0.03806 -0.02915 0
1 57 0.05156 -0.03281 0
1 58 0.06699 -0.03582 0
1 59 0.08427 -0.03817 0
1 60 0.10332 -0.03991 0
1 61 0.12408 -0.04106 0
1 62 0.14645 -0.04166 0
1 63 0.17033 -0.04177 0
1 64 0.19562 -0.04147 0
1 65 0.22221 -0.04078 0
1 66 0.25000 -0.03974 0
1 67 0.27886 -0.03845 0
1 68 0.30866 -0.03700 0
1 69 0.33928 -0.03547 0
1 70 0.37059 -0.03390 0
1 71 0.40245 -0.03229 0
1 72 0.43474 -0.03063 0
1 73 0.46730 -0.02891 0
1 74 0.50000 -0.02713 0
1 75 0.53270 -0.02529 0
1 76 0.56526 -0.02340 0
1 77 0.59755 -0.02149 0
1 78 0.62941 -0.01958 0
1 79 0.66072 -0.01772 0
1 80 0.69134 -0.01596 0
1 81 0.72114 -0.01430 0
1 82 0.75000 -0.01277 0
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1 83 0.77779 -0.01136 0
1 84 0.80438 -0.01006 0
1 85 0.82967 -0.00886 0
1 86 0.85355 -0.00775 0
1 87 0.87592 -0.00674 0
1 88 0.89668 -0.00583 0
1 89 0.91573 -0.00502 0
1 90 0.93301 -0.00431 0
1 91 0.94844 -0.00364 0
1 92 0.96194 -0.00297 0
1 93 0.97347 -0.00227 0
1 94 0.98296 -0.00156 0
1 95 0.99039 -0.00092 0
1 96 0.99572 -0.00042 0
1 97 0.99893 -0.00011 0
MATERIAL PROPERTY
Material 1 – Air
Isentropic Relative Permeability of air =1
Material 2 – Aluminum alloy
Properties of aluminum alloy:
Density = 2770 kg m-3
Young's Modulus = 71x 109 Pa
Poisson's Ratio = 0.33
Tensile Yield Strength = 28x107 Pa
Tensile Ultimate Strength = 31x107 Pa
Specific Heat = 875 J kg-1 C
-1
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MESHING
The Blue colour surface indicates Air Inlet
The Red colour surface indicates Air Outlet
The White colour body indicates the Aerofoil
The remaining four yellow colour surfaces are symmetrical and acts as a wall
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Fig 1
Fig 1 shows the meshing of whole body i.e. the aerofoil and the close surface.
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Fig 2
Fig 2 represents the closer view of meshed Aerofoil.
Total no. of nodes = 96477
Total no. of elements = 543160
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Details of meshing
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BOUNDARY CONDITIONS
FOR FLUENT
The front surface is assumed as the Velocity inlet and the rear surface is
assumed as the pressure outlet.
The inlet velocity of air is defined as 138 m/s and the pressure at the exit is
set as 0 Pascal.
Number of iterations is set as 100
FOR STATIC STRUCTURAL ANALYSIS
1. Fixed support
The Scoping method is changed to Named selection from geometry selection.
Fixed support is assigned to the Connection face of Wing.
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2. Fluid Solid Interface
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RESULTS
FLUENT
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Contour option is selected from the Fluent window and
the left surface is selected from the pop up window.
Display tab is clicked for the result.
And the contours of static pressure are observed.
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A plane is created with co-ordinates
X1= 0 y1=0 z1= -5
X2= 5 y2=0 z1= -5
X3= 0 y1= 5 z1= -5
And the contours of static pressure are observed.
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A plane is created with co-ordinates
X1= 0 y1=0 z1= -7
X2= 5 y2=0 z1= -7
X3= 0 y1= 5 z1= -7
And the contours of static pressure are observed.
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A plane is created with co-ordinates
X1= 0 y1=0 z1= -8
X2= 5 y2=0 z1= -8
X3= 0 y1= 5 z1= -8
And the contours of static pressure are observed.
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Isometric View of the Aerofoil.
The contours of static pressure are observed.
The static pressure has low values as it extends from left to
right from the top surface of the aerofoil.
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Isometric View 2 of the Aerofoil.
The contours of static pressure are observed.
The static pressure has maximum value at the bottom
surface of the aerofoil.
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Vectors option is selected from the Fluent window and the
left surface is selected from the pop up window. Display
tab is clicked for the result.
And the velocity vectors colored by Velocity magnitude
(m/s) are observed.
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A plane is created with co-ordinates
X1= 0 y1=0 z1= -5
X2= 5 y2=0 z1= -5
X3= 0 y1= 5 z1= -5
And the velocity vectors colored by Velocity magnitude in
m/s are observed.
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A plane is created with co-ordinates
X1= 0 y1=0 z1= -7
X2= 5 y2=0 z1= -7
X3= 0 y1= 5 z1= -7
And the velocity vectors colored by Velocity magnitude in
m/s are observed.
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STRUCTURAL First Saved Monday, October 13, 2014
Last Saved Monday, October 13, 2014
Product Version 14.0 Release
Save Project Before Solution No
Save Project After Solution No
TABLE 1
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Unit System Metric (m, kg, N, s, V, A) Degrees rad/s Celsius
Angle Degrees
Rotational Velocity rad/s
Temperature Celsius
Model (C4)
Geometry
TABLE 2 Model (C4) > Geometry
Object Name Geometry
State Fully Defined
Definition
Source E:\ANSYS WORKBENCH\Nithin Devasia\ANSYS Project\CFD and Structural
Analysis of NACA 4415 Aerofoil_files\dp0\Geom\DM\Geom.agdb
Type DesignModeler
Length Unit Millimeters
Element Control Program Controlled
Display Style Body Color
Bounding Box
Length X 17.324 m
Length Y 8.5843 m
Length Z 10. m
Properties
Volume 0.12124 m³
Mass 335.83 kg
Scale Factor Value 1.
Statistics
Bodies 2
Active Bodies 1
Nodes 76553
Elements 39122
Mesh Metric None
Basic Geometry Options
Parameters Yes
Parameter Key DS
Attributes No
Named Selections No
Material Properties No
Advanced Geometry Options
Use Associativity Yes
Coordinate Systems No
Reader Mode Saves Updated File
No
Use Instances Yes
Smart CAD Update No
Attach File Via Temp File
Yes
Temporary Directory C:\Users\SDA\AppData\Roaming\Ansys\v140
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Analysis Type 3-D
Decompose Disjoint Faces
Yes
Enclosure and Symmetry
Processing Yes
TABLE 3 Model (C4) > Geometry > Parts
Object Name WING AIR
State Meshed Suppressed
Graphics Properties
Visible Yes No
Transparency 1
Definition
Suppressed No Yes
Stiffness Behavior Flexible
Coordinate System Default Coordinate System
Reference Temperature By Environment
Material
Assignment Aluminum Alloy Structural Steel
Nonlinear Effects Yes
Thermal Strain Effects Yes
Bounding Box
Length X 1.8088 m 17.324 m
Length Y 0.34196 m 8.5843 m
Length Z 7. m 10. m
Properties
Volume 0.12124 m³ 1484.7 m³
Mass 335.83 kg 1.1655e+007 kg
Centroid X 0.84176 m 0.32265 m
Centroid Y -2.9072e-002 m 0.4867 m
Centroid Z -3.4821 m -5.0024 m
Moment of Inertia Ip1 1686.2 kg·m² 1.6885e+008 kg·m²
Moment of Inertia Ip2 1782.8 kg·m² 3.8912e+008 kg·m²
Moment of Inertia Ip3 103.51 kg·m² 3.6364e+008 kg·m²
Statistics
Nodes 76553 0
Elements 39122 0
Mesh Metric None
Coordinate Systems
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TABLE 4 Model (C4) > Coordinate Systems > Coordinate System
Object Name Global Coordinate System
State Fully Defined
Definition
Type Cartesian
Coordinate System ID 0.
Origin
Origin X 0. m
Origin Y 0. m
Origin Z 0. m
Directional Vectors
X Axis Data [ 1. 0. 0. ]
Y Axis Data [ 0. 1. 0. ]
Z Axis Data [ 0. 0. 1. ]
Connections
TABLE 5 Model (C4) > Connections
Object Name Connections
State Fully Defined
Auto Detection
Generate Automatic Connection On Refresh Yes
Transparency
Enabled Yes
TABLE 6 Model (C4) > Connections > Contacts
Object Name Contacts
State Suppressed
Definition
Connection Type Contact
Scope
Scoping Method Geometry Selection
Geometry All Bodies
Auto Detection
Tolerance Type Slider
Tolerance Slider 0.
Tolerance Value 5.4418e-002 m
Use Range No
Face/Face Yes
Face/Edge No
Edge/Edge No
Priority Include All
Group By Bodies
Search Across Bodies
TABLE 7 Model (C4) > Connections > Contacts > Contact Regions
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Object Name Contact Region
State Suppressed
Scope
Scoping Method Geometry Selection
Contact 5 Faces
Target No Selection
Contact Bodies WING
Target Bodies AIR
Definition
Type Bonded
Scope Mode Automatic
Behavior Program Controlled
Suppressed No
Advanced
Formulation Program Controlled
Detection Method Program Controlled
Normal Stiffness Program Controlled
Update Stiffness Program Controlled
Pinball Region Program Controlled
Mesh
TABLE 8 Model (C4) > Mesh
Object Name Mesh
State Solved
Defaults
Physics Preference Mechanical
Relevance 0
Sizing
Use Advanced Size Function Off
Relevance Center Coarse
Element Size Default
Initial Size Seed Active Assembly
Smoothing Medium
Transition Fast
Span Angle Center Coarse
Minimum Edge Length 5.e-003 m
Inflation
Use Automatic Inflation None
Inflation Option Smooth Transition
Transition Ratio 0.272
Maximum Layers 5
Growth Rate 1.2
Inflation Algorithm Pre
View Advanced Options No
Patch Conforming Options
Triangle Surface Mesher Program Controlled
Advanced
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Shape Checking Standard Mechanical
Element Midside Nodes Program Controlled
Straight Sided Elements No
Number of Retries Default (4)
Extra Retries For Assembly Yes
Rigid Body Behavior Dimensionally Reduced
Mesh Morphing Disabled
Defeaturing
Pinch Tolerance Please Define
Generate Pinch on Refresh No
Automatic Mesh Based Defeaturing On
Defeaturing Tolerance Default
Statistics
Nodes 76553
Elements 39122
Mesh Metric None
Named Selections
TABLE 9 Model (C4) > Named Selections > Named Selections
Object Name ConnectionFaceofWing WingPeripherals Aircontcatsurafce AirInlet AirOutlet
State Fully Defined Suppressed
Scope
Scoping Method Geometry Selection
Geometry 1 Face 3 Faces No Selection
Definition
Send to Solver Yes
Visible Yes
Program Controlled Inflation
Exclude
Statistics
Type Imported
Total Selection 1 Face 3 Faces 1 Face
Suppressed 0 3 1
Used by Mesh Worksheet No
TABLE 10 Model (C4) > Named Selections > Named Selections
Object Name LeftSurface Toprightbottomsurfaces
State Suppressed
Scope
Scoping Method Geometry Selection
Geometry No Selection
Definition
Send to Solver Yes
Visible Yes
Program Controlled Inflation Exclude
Statistics
Type Imported
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Total Selection 1 Face 3 Faces
Suppressed 1 3
Used by Mesh Worksheet No
Static Structural (C5)
TABLE 11 Model (C4) > Analysis
Object Name Static Structural (C5)
State Solved
Definition
Physics Type Structural
Analysis Type Static Structural
Solver Target Mechanical APDL
Options
Environment Temperature 22. °C
Generate Input Only No
TABLE 12 Model (C4) > Static Structural (C5) > Analysis Settings
Object Name Analysis Settings
State Fully Defined
Restart Analysis
Restart Type Program Controlled
Status Done
Step Controls
Number Of Steps 1.
Current Step Number 1.
Step End Time 1. s
Auto Time Stepping Program Controlled
Solver Controls
Solver Type Program Controlled
Weak Springs Program Controlled
Large Deflection Off
Inertia Relief Off
Restart Controls
Generate Restart Points
Program Controlled
Retain Files After Full Solve
Yes
Nonlinear Controls
Force Convergence Program Controlled
Moment Convergence
Program Controlled
Displacement Convergence
Program Controlled
Rotation Convergence
Program Controlled
Line Search Program Controlled
Stabilization Off
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Output Controls
Stress Yes
Strain Yes
Nodal Forces No
Contact Miscellaneous
No
General Miscellaneous
No
Calculate Results At All Time Points
Max Number of Result Sets
Program Controlled
Analysis Data Management
Solver Files Directory E:\ANSYS WORKBENCH\Nithin Devasia\ANSYS Project\CFD and Structural
Analysis of NACA 4415 Aerofoil_files\dp0\SYS\MECH\
Future Analysis None
Scratch Solver Files Directory
Save MAPDL db No
Delete Unneeded Files
Yes
Nonlinear Solution No
Solver Units Active System
Solver Unit System mks
TABLE 13 Model (C4) > Static Structural (C5) > Loads
Object Name Fixed Support Fluid Solid Interface
State Fully Defined
Scope
Scoping Method Named Selection
Named Selection ConnectionFaceofWing WingPeripherals
Definition
Type Fixed Support Fluid Solid Interface
Suppressed No
Interface Number 1.
Solution (C6)
TABLE 14 Model (C4) > Static Structural (C5) > Solution
Object Name Solution (C6)
State Solved
Adaptive Mesh Refinement
Max Refinement Loops 1.
Refinement Depth 2.
Information
Status Done
TABLE 15
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Model (C4) > Static Structural (C5) > Solution (C6) > Solution Information
Object Name Solution Information
State Solved
Solution Information
Solution Output Solver Output
Newton-Raphson Residuals 0
Update Interval 2.5 s
Display Points All
FE Connection Visibility
Activate Visibility Yes
Display All FE Connectors
Draw Connections Attached To All Nodes
Line Color Connection Type
Visible on Results No
Line Thickness Single
Display Type Lines
TABLE 16 Model (C4) > Static Structural (C5) > Solution (C6) > Results
Object Name Equivalent Stress Maximum Principal
Stress Minimum Principal
Stress Total
Deformation
State Solved
Scope
Scoping Method Geometry Selection
Geometry 1 Face All Bodies
Definition
Type Equivalent (von-Mises)
Stress Maximum Principal
Stress Minimum Principal
Stress Total
Deformation
By Time
Display Time Last
Calculate Time History
Yes
Identifier
Suppressed No
Integration Point Results
Display Option Averaged
Results
Minimum 31980 Pa -7.1972e+007 Pa -3.9676e+008 Pa 0. m
Maximum 2.6611e+008 Pa 4.2613e+008 Pa 1.2876e+008 Pa 0.41933 m
Information
Time 1. s
Load Step 1
Substep 1
Iteration Number 5
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FIGURE 1 Model (C4) > Static Structural (C5) > Solution (C6) > Equivalent Stress > Image
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FIGURE 2 Model (C4) > Static Structural (C5) > Solution (C6) > Maximum Principal Stress > Image
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FIGURE 3 Model (C4) > Static Structural (C5) > Solution (C6) > Minimum Principal Stress > Image
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FIGURE 4
Model (C4) > Static Structural (C5) > Solution (C6) > Total Deformation > Image
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TABLE 17
Model (C4) > Static Structural (C5) > Solution (C6) > Probes
Object Name Force Reaction Moment Reaction
State Solved
Definition
Type Force Reaction Moment Reaction
Location Method Boundary Condition
Boundary Condition Fixed Support
Orientation Global Coordinate System
Suppressed No
Summation Centroid
Options
Result Selection All
Display Time End Time
Results
X Axis -4909.8 N -4.1227e+005 N·m
Y Axis -1.2853e+005 N 19599 N·m
Z Axis 1530.7 N 19913 N·m
Total 1.2863e+005 N 4.1322e+005 N·m
Maximum Value Over Time
X Axis -4909.8 N -4.1227e+005 N·m
Y Axis -1.2853e+005 N 19599 N·m
Z Axis 1530.7 N 19913 N·m
Total 1.2863e+005 N 4.1322e+005 N·m
Minimum Value Over Time
X Axis -4909.8 N -4.1227e+005 N·m
Y Axis -1.2853e+005 N 19599 N·m
Z Axis 1530.7 N 19913 N·m
Total 1.2863e+005 N 4.1322e+005 N·m
Information
Time 1. s
Load Step 1
Substep 1
Iteration Number 5
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FIGURE 5
Model (C4) > Static Structural (C5) > Solution (C6) > Force Reaction > Image
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FIGURE 6
Model (C4) > Static Structural (C5) > Solution (C6) > Moment Reaction > Image
Material Data
Aluminum Alloy
TABLE 18 Aluminum Alloy > Constants
Density 2770 kg m^-3
Coefficient of Thermal Expansion 2.3e-005 C^-1
Specific Heat 875 J kg^-1 C^-1
TABLE 19 Aluminum Alloy > Compressive Ultimate Strength
Compressive Ultimate Strength Pa
0
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TABLE 20 Aluminum Alloy > Compressive Yield Strength
Compressive Yield Strength Pa
2.8e+008
TABLE 21 Aluminum Alloy > Tensile Yield Strength
Tensile Yield Strength Pa
2.8e+008
TABLE 22 Aluminum Alloy > Tensile Ultimate Strength
Tensile Ultimate Strength Pa
3.1e+008
TABLE 23 Aluminum Alloy > Isotropic Secant Coefficient of Thermal Expansion
Reference Temperature C
22
TABLE 24 Aluminum Alloy > Isotropic Thermal Conductivity
Thermal Conductivity W m^-1 C^-1 Temperature C
114 -100
144 0
165 100
175 200
TABLE 25 Aluminum Alloy > Alternating Stress R-Ratio
Alternating Stress Pa Cycles R-Ratio
2.758e+008 1700 -1
2.413e+008 5000 -1
2.068e+008 34000 -1
1.724e+008 1.4e+005 -1
1.379e+008 8.e+005 -1
1.172e+008 2.4e+006 -1
8.963e+007 5.5e+007 -1
8.274e+007 1.e+008 -1
1.706e+008 50000 -0.5
1.396e+008 3.5e+005 -0.5
1.086e+008 3.7e+006 -0.5
8.791e+007 1.4e+007 -0.5
7.757e+007 5.e+007 -0.5
7.239e+007 1.e+008 -0.5
1.448e+008 50000 0
1.207e+008 1.9e+005 0
1.034e+008 1.3e+006 0
9.308e+007 4.4e+006 0
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8.618e+007 1.2e+007 0
7.239e+007 1.e+008 0
7.412e+007 3.e+005 0.5
7.067e+007 1.5e+006 0.5
6.636e+007 1.2e+007 0.5
6.205e+007 1.e+008 0.5
TABLE 26 Aluminum Alloy > Isotropic Resistivity
Resistivity ohm m Temperature C
2.43e-008 0
2.67e-008 20
3.63e-008 100
TABLE 27 Aluminum Alloy > Isotropic Elasticity
Temperature C Young's Modulus Pa Poisson's Ratio Bulk Modulus Pa Shear Modulus Pa
7.1e+010 0.33 6.9608e+010 2.6692e+010
TABLE 28 Aluminum Alloy > Isotropic Relative Permeability
Relative Permeability
1
Structural Steel
TABLE 29 Structural Steel > Constants
Density 7850 kg m^-3
Coefficient of Thermal Expansion 1.2e-005 C^-1
Specific Heat 434 J kg^-1 C^-1
Thermal Conductivity 60.5 W m^-1 C^-1
Resistivity 1.7e-007 ohm m
TABLE 30 Structural Steel > Compressive Ultimate Strength
Compressive Ultimate Strength Pa
0
TABLE 31 Structural Steel > Compressive Yield Strength
Compressive Yield Strength Pa
2.5e+008
TABLE 32 Structural Steel > Tensile Yield Strength
Tensile Yield Strength Pa
2.5e+008
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TABLE 33 Structural Steel > Tensile Ultimate Strength
Tensile Ultimate Strength Pa
4.6e+008
TABLE 34 Structural Steel > Isotropic Secant Coefficient of Thermal Expansion
Reference Temperature C
22
TABLE 35 Structural Steel > Alternating Stress Mean Stress
Alternating Stress Pa Cycles Mean Stress Pa
3.999e+009 10 0
2.827e+009 20 0
1.896e+009 50 0
1.413e+009 100 0
1.069e+009 200 0
4.41e+008 2000 0
2.62e+008 10000 0
2.14e+008 20000 0
1.38e+008 1.e+005 0
1.14e+008 2.e+005 0
8.62e+007 1.e+006 0
TABLE 36 Structural Steel > Strain-Life Parameters
Strength Coefficient Pa
Strength Exponent
Ductility Coefficient
Ductility Exponent
Cyclic Strength Coefficient Pa
Cyclic Strain Hardening Exponent
9.2e+008 -0.106 0.213 -0.47 1.e+009 0.2
TABLE 37 Structural Steel > Isotropic Elasticity
Temperature C Young's Modulus Pa Poisson's Ratio Bulk Modulus Pa Shear Modulus Pa
2.e+011 0.3 1.6667e+011 7.6923e+010
TABLE 38
Structural Steel > Isotropic Relative Permeability
Relative Permeability
10000
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INFERENCE
From the Fluid flow analysis it is observed that the maximum value of static
pressure which is exerted by the air on the surface of the aerofoil is 12600 Pascal
and the maximum magnitude of velocity of air leaving from the surface of aerofoil
is found to be 235 m/s. So according to the protocols of National Advisory
Committee for Aeronautics, the value of Static pressure and Magnitude of velocity
are under the permissible limits and hence the design is fluid dynamically safe,
hence for finding out the structural stability of the design, a static structural
analysis coupled with Workbench system coupling is conducted and the values of
Equivalent stress, Maximum and Minimum Principal Stress, Total deformation,
Force and Moment reactions are obtained.
The maximum value of Von misses stress is found out to be 266.11 MPa,
Maximum principal stress is 426.13 MPa, Minimum principal stress is 128.76 MPa
and Maximum deformation is 419.33 mm.
The above obtained values are within the desired limits according to National
Advisory Committee for Aeronautics (NACA), hence the design is structurally
safe.
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SUGGESTIONS AND CONCLUSIONS
The fluid flow and structural analysis can be carried out for a different value of the
inlet air velocity and the angle of attack and camber angle may be changed in order
to get different result.
Fluid flow and Structural analysis of NACA 4515 Aerofoil is carried out with
Ansys Workbench and the required results are obtained. The results are found
successful and the aerofoil can be used for practical application.
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REFERENCE
NACA Aerofoil – Wikipedia
Aerofoil – Wikipedia
Ansys Workbench Reference guide
Ansys Design Exploration – Ansys Inc.
NACA 4 digit profile generator
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