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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:


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


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


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.


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,


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.


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).


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


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

CADD Centre Thiruvananthapuram | Ansys Workbench |

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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.


15

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.


19

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.


20

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.


21

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


22

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


23

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


24

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


25

Fig 1

Fig 1 shows the meshing of whole body i.e. the aerofoil and the close surface.


26

Fig 2

Fig 2 represents the closer view of meshed Aerofoil.

Total no. of nodes = 96477

Total no. of elements = 543160


27

Details of meshing


28

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.


29

2. Fluid Solid Interface


30


31

RESULTS

FLUENT


32

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.


33

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



34


X1= 0 y1=0 z1= -7

X2= 5 y2=0 z1= -7

X3= 0 y1= 5 z1= -7



35


X1= 0 y1=0 z1= -8

X2= 5 y2=0 z1= -8

X3= 0 y1= 5 z1= -8



36

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.


37

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.


38

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.


39


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.


40


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.


41

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


42

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


43

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



Statistics

Nodes 76553 0

Elements 39122 0

Mesh Metric None

Coordinate Systems


44

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


45

Object Name Contact Region

State Suppressed

Scope


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


46

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


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


Geometry No Selection

Definition

Send to Solver Yes

Visible Yes

Program Controlled Inflation Exclude

Statistics

Type Imported


47

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


48

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


49

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


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


50

FIGURE 1 Model (C4) > Static Structural (C5) > Solution (C6) > Equivalent Stress > Image


51

FIGURE 2 Model (C4) > Static Structural (C5) > Solution (C6) > Maximum Principal Stress > Image


52

FIGURE 3 Model (C4) > Static Structural (C5) > Solution (C6) > Minimum Principal Stress > Image


53

FIGURE 4

Model (C4) > Static Structural (C5) > Solution (C6) > Total Deformation > Image


54

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


55

FIGURE 5

Model (C4) > Static Structural (C5) > Solution (C6) > Force Reaction > Image


56

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


57

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


58

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


59

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


60

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.


61

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.


62

REFERENCE

NACA Aerofoil – Wikipedia

Aerofoil – Wikipedia

Ansys Workbench Reference guide

Ansys Design Exploration – Ansys Inc.

NACA 4 digit profile generator