ANALYSIS OF WING LOCATION ON

AERODYNAMIC PERFORMANCE OF AIRPLANE

A Project Report
Submitted in the partial fulfilment of the requirements for the Award of the
Degree of
BACHELOR OF TECHNOLOGY
In
MECHANICAL ENGINEERING
Submitted By

B. DEMUDU BABU 21475A0323

D. CHANDU 21475A0324
R. SAI 21475A0331
B. RAMANJANEYULU 20471A0358
S. RANENDRA VAMSHI 20471A0371

Under the guidance of

Dr. D. JAGADISH M.Tech, Ph.D.
Professor
DEPARTMENT OF MECHANICAL ENGINEERING

Narasaraopet 522601, Andhra Pradesh, India

April 2024
 DECLERATION

The Project entitled “ ANALYSIS OF WING LOCATION ON AERODYNAMIC

PERFORMANCE OF AIRPLANE ” is a record of bonafied work carried out by us,
submitted in partial fulfilment for the award of B. Tech in MECHANICAL
ENGINEERING to the Jawaharlal Nehru Technological University Kakinada, Kakinada.
This report has not been submitted to any other University or Institute for the award of any
degree or diploma.

B.DEMUDU BABU - (21475A0323)

D.CHANDU - (21475A0324)
R.SAI - (21475A0331)
B.RAMANJANEYULU - (20471A0358)
S.RANENDRA VAMSHI - (20471A0371)

Signature of candidates

I
 CERTIFICATE
This is to certify that the Project entitled “ ANALYSIS OF WING LOCATION
ON AERODYNAMIC PERFORMANCE OF AIRPLANE ” is being submitted by Mr.
B.DEMUDU BABU (21475A0323), Mr. D.CHANDU (21475A0324), Mr. R.SAI
(21475A0331), Mr. B.RAMANJANEYULU (20471A0358), Mr. S.RANENDRA
VAMSHI (20471A0371) in partial fulfilment for the award of B. Tech in MECHANICAL
ENGINEERING to the Jawaharlal Nehru Technological University Kakinada, is a record
of bonafied work carried out by them under our guidance and supervision.

The results embodied in this is have not been submitted to any other University or
Institute for the award of any degree or diploma.

Signature of the Guide Signature of the HOD

Dr. D. Jagadish Dr. B. Venkata Siva

M. Tech, Ph.D M. Tech, Ph.D.,FIE(I),MISTE,ASME

Professor Professor & HOD

Internal Examiner External Examiner

II
 ACKNOWLEDGEMENT
It is our pleasure to express our deep and sincere gratitude to our Project Guide
Dr.D. Jagadish, Assistant Professor/ Associate Professor, for extending her sincere and
heartfelt guidance throughout this project work.

We greatly indebted to Dr. B. Venkata Shiva, Professor & Head of the

Department, for providing motivation and valuable suggestions at every stage of our
course of study.

We Convey our special thankful to beloved principal Dr. M. Sreenivasa Kumar

for providing us sparkling environment during our course of study.

We are thankful to our vice principle Dr. D. Suneel for providing excellent lab
facilities for the project.

We also express sincere thanks to Sri M.V. Koteswara Rao, Chairman of

Narasaraopeta Engineering College, Narasaraopet for providing excellent infrastructural
facilities to complete our course.

We extend our sincere thanks to all other Teaching and Non-Teaching Faculty
members of the department for their cooperation and encouragement throughout our
course ofstudy.

We affectionately acknowledge our friends for their motivation and suggestions

whichhelps us in successfully completing our course.

We have no words to acknowledge the warm affection, constant inspiration and

encouragement that we received from our Parents and Family Members.

III
 ABSTRACT

The study focuses on investigating the impact of wing location on the aerodynamic
performance of an airplane, employing computational analysis through XFLR5 software.
The positioning of wings plays a crucial role in determining the aircraft's efficiency,
stability, and overall flight characteristics. Utilizing XFLR5, a powerful tool for airfoil and
wing analysis, the research involves simulating various wing configurations and their
effects on lift, drag, and overall aerodynamic behavior.

The methodology involves systematically altering the wing location and assessing
key aerodynamic parameters. By analyzing lift-to-drag ratios, stall characteristics, and
other performance indicators, the study aims to optimize wing placement for enhanced
flight performance. XFLR5 allows for the visualization of aerodynamic forces and
moments, providing valuable insights into the intricate relationship between wing location
and aircraft dynamics.

The study of wing location in relation to the aerodynamic performance of an

airplane is a critical and complex aspect of aircraft design. The position of the wings
significantly influences the overall aerodynamic characteristics, affecting key parameters
such as lift, drag, stability, and maneuverability. Through systematic investigation and
analysis, researchers and engineers can gain valuable insights into the optimal wing
placement for different types of aircraft and missions.

If it observed that lift is more in rectangular wing at High wing configuration. i.e.,
lift of 6N and drag of 3.8N is Observed.

If it observed that lift is more in swept back wing at Low wing configuration. i.e.,
lift of 1N and drag of 0.8N is Observed.

If it observed that lift is more in delta wing at Mid wing configuration. i.e., lift of
1N and drag of 0.6N is Observed.

IV
 CONTENTS

DESCRIPTION: PAGE NO
DECLERATION I
CERTIFICATE II
ACKNOWLEDGEMENT III
ABSTRACT IV

CHAPTER 1: INTRODUCTION 1 - 10
1.1 IMPORTANCE OF XFLR5 1
1.2 KEY FEATURES OF XFLR5 1
1.3 WHAT IS AERODYNAMICS 2
1.4 WHAT IS AIRFOIL 2
1.5 AIRFOIL THEORY 3
1.6 TYPES OF AIRFOIL 4
1.7 TYPES OF WINGS 6
1.8 TYPES OF WING LOCATIONS 8
1.9 LIFT THEORY 9
1.10 WHAT IS LIFT AND DRAG 10

CHAPTER 2: LITERATURE REVIEW 11 - 11

CHAPTER 3: DESIGN AND ANALYSIS OF AIRFOIL 12 - 14
3.1 AIRFOIL AND TYPES OF AIRFOIL 12
3.2 DESIGNING OF AIRFOIL 12
3.3 ANALYSIS OF AIRFOIL 13

CHAPTER 4: DESIGN AND ANALYSIS OF WING

LOCATIONS 15 - 17
4.1 WING LOCATIONS AND TYPES OF WING LOCATIONS 15
4.2 DESIGNING OF WING LOCATIONS 15
4.3 ANALYSIS OF WING LOCATIONS 17

V
CHAPTER 5: TESTING METHODS, PROCEDURE
AND WING LOCATIONS REPORT 18 – 33
5.1 TESTING METHODS 18
5.2 EXPERIMENTAL PROCEDURE 20
5.3 WING LOCATIONS REPORT 22

CHAPTER 6: CONCLUSION 34 - 34
CHAPTER 7: REFERENCE 35 - 35
CHAPTER 8: GROUP PHOTOS 36 - 36

VI
 LIST OF FIGURES
S.No. Description Page No.
1. Airfoil / Aerofoil Shape 3

2. Different Types of Airfoil Designs 5

3. Different Types of Wings 7

4. Types of Wing Locations 9

5. Lift and Drag 10

6. The Figure shows different airfoils designed in XFLR5 13

7. The Figure shows different airfoils Analysis in XFLR5 14

8. The Figure shows wing at above Y-Axis 16

9. The Figure shows wing on Y-Axis 16

10. The Figure shows wing at below Y-Axis 17

11. The Figure shows Analysis of wing at different locations 17

12. Airfoil Analysis 22

13. The figure shows High-Wing Configuration in Rectangular wing 23

14. The figure shows Mid-Wing Configuration in Rectangular wing 23

15. The figure shows Low-Wing Configuration in Rectangular wing 24

16. The figure shows comparison between High, Mid, Low wings

in Rectangular wing 25

17. The figure shows High-Wing Configuration in Sweptback Wing 26

18. The figure shows Mid-Wing Configuration in Sweptback Wing 27

19. The figure shows Low-Wing Configuration in Sweptback Wing 27

20. The figure shows comparison between High, Mid, Low wings

in Sweptback wing 28

21. The figure shows High-Wing Configuration in Delta Wing 29

22. The figure shows Mid-Wing Configuration in Delta Wing 30

23. The figure shows Low-Wing Configuration in Delta Wing 31

VII
24. The figure shows comparison between High, Mid, Low wings

in Delta wing 32

25. Group Photo 36

VIII
 CHAPTER 1
INTRODUCTION
1.1 Importance of XFLR5:
Flying Wing Design and Analysis XFLR5 is software that enables 2D and 3D
aerodynamic analysis of bodies and bearing areas, separately or jointly. The software makes
analysis for small Reynolds numbers.

The importance of XFLR5 in aerospace engineering lies in its ability to demystify

the complexities of aerodynamics, offering a versatile and accessible platform for airfoil
and wing analysis. From educational settings to cutting-edge research labs , XFLR5 is
instrumental in shaping the future of aircraft design and performance.

1.2 Key Features of XFLR5:

XFLR5 is a software tool designed for the analysis and design of airfoils and wings.
Here are some key features of XFLR5:

1. Airfoil Analysis: XFLR5 allows users to analyze the aerodynamic characteristics

of different airfoil shapes. This includes studying lift, drag, and pitching moment
coefficients over a range of angles of attack and airspeeds.
2. Polar Diagrams: The software generates polar diagrams that illustrate the
performance of an airfoil under various conditions. These diagrams provide a visual
representation of how lift and drag vary with changes in angle of attack and
airspeed.
3. Wing Analysis: XFLR5 extends its capabilities to analyse entire wings, allowing
users to study the aerodynamic behavior of wing configurations. This is important
for aircraft design and optimization.
4. Flight Simulation: The software includes features for simulating the flight
behavior of an aircraft based on the analyzed aerodynamic data. This helps in
predicting the overall performance of an aircraft, including stability and control
characteristics.
5. Airfoil and Wing Design: XFLR5 supports airfoil and wing design by allowing
users to modify and optimize shapes. Engineers can experiment with different

1
 parameters to achieve specific aerodynamic goals, such as maximizing lift or
minimizing drag.
6. Inverse Design: The software offers inverse design capabilities, enabling users to
specify desired aerodynamic characteristics, and the software will attempt to
generate an airfoil or wing shape that meets those criteria.
7. Graphical User Interface (GUI): XFLR5 features a user-friendly graphical
interface, making it accessible to users who may not have extensive programming
or computational fluid dynamics (CFD) experience. The GUI facilitates the input
of parameters and visualization of results.
8. Vortex Panel Method: The underlying computational method in XFLR5 is often
based on a vortex panel method. This numerical approach is used to model the
aerodynamic forces acting on airfoils and wings.
9. Stability and Control Analysis: XFLR5 can be used to assess the stability and
control characteristics of an aircraft. This is crucial for ensuring that the aircraft is
controllable and stable under different operating conditions.
10. Educational Use: XFLR5 is commonly used as an educational tool in aerospace
engineering programs to teach students about aerodynamics and aircraft design.

These are the key future of XFLR5 software.

1.3 What is Aerodynamics?

Aerodynamics is the study of the behavior of air as it interacts with solid objects,
such as aircraft, cars, buildings, and other structures. It is a branch of fluid dynamics that
specifically focuses on the properties of air and how they affect objects moving through it.
The primary goals of aerodynamics are to understand, analyze, and predict the forces and
movements of air and objects in motion.

1.4 What is Airfoil?

An airfoil, also known as aerofoil, is a shape designed to produce aerodynamic lift
when air flows over it. Airfoils are a fundamental component of wings, blades, and other
surfaces on vehicles such as airplanes, helicopters, wind turbines, and propellers. The shape
of an airfoil is crucial in determining the aerodynamic forces acting on it as it moves
through the air.

2
1.5 Airfoil Theory:
The airfoil theory is a fundamental concept in aerodynamics that explains the
generation of lift by aircraft wings. An airfoil is the cross-sectional shape of a wing, blade,
or any other body designed to produce lift when moving through air. Here are the key points
related to airfoil theory:

Fig 1: Airfoil / Aerofoil Shape

1. Airfoil Shape: Airfoils are designed with a specific shape to achieve efficient lift.
The upper surface is usually curved, while the lower surface is relatively flat. This
shape is crucial for exploiting Bernoulli's principle and creating a pressure
difference.
2. Bernoulli’s Principle: According to Bernoulli's principle, as the speed of a fluid
(such as air) increases, its pressure decreases. In the context of an airfoil, the shape
causes the air on the upper surface to travel faster than the air on the lower surface,
creating lower pressure on top and higher pressure on the bottom, resulting in lift.
3. Leading Edge: The leading edge is the front edge of the airfoil, facing into the
oncoming air. It is a critical part of the airfoil's shape and can be either rounded or
sharp, depending on the specific design requirements.
4. Trailing Edge: The trailing edge is the rear edge of the airfoil, opposite the leading
edge. It is also an essential aspect of the airfoil's design, and its shape influences the
aerodynamic characteristics of the airfoil.

3
 5. Chord Line: The chord line is an imaginary straight line connecting the leading
and trailing edges of the airfoil. The length of this line is the chord length, and it
serves as a reference for various aerodynamic calculations.
6. Camber: Camber is the curvature of the airfoil's upper and lower surfaces. An
airfoil can be either cambered (curved) or symmetric (flat). Camber contributes to
lift generation by creating pressure differences between the upper and lower
surfaces.
7. Angle of Attack: The angle of attack is the angle between the chord line of the
airfoil and the oncoming air. It plays a crucial role in determining the lift and drag
forces acting on the airfoil.
8. Upper Surface and Lower Surface: The airfoil has an upper surface and a lower
surface. Air flows over these surfaces, and the pressure distribution between them
creates lift. The shape of these surfaces, in conjunction with the camber, contributes
to the overall aerodynamic performance.
9. Computational Fluid Dynamics (CFD): Advanced tools like Computational Fluid
Dynamics are used to simulate and analyze the complex airflow around airfoils.
This helps in designing and optimizing airfoil shapes for specific performance
requirements.

Understanding airfoil theory is essential for designing efficient and stable aircraft.
Engineers use this theory to optimize wing shapes, ensuring a balance between lift,
drag, and other aerodynamic factors for safe and effective flight.

1.6 TYPES OF AIRFOIL:

Airfoils, also known as aerofoils, are the cross-sectional shapes of wings, blades,
or other surfaces designed to provide lift when moving through a fluid, such as air. There
are various types of airfoils, each with unique characteristics suited for specific
applications. Here are some common types of airfoils:

4
 Fig 2: Different Types of Airfoil Designs

1. Symmetrical Airfoil: A symmetrical airfoil has the same shape on the top and
bottom surfaces. The chord line (an imaginary line from the leading edge to the
trailing edge) is centered, and the camber (curvature) is symmetric. Symmetrical
airfoils are often used in applications where lift is not the primary concern, such as
in the tail surfaces of many aircraft.
2. Asymmetrical (Cambered) Airfoil: An asymmetrical or cambered airfoil has a
curved shape, with the upper surface typically more curved than the lower surface.
This design creates different lengths for the paths air travels over and under the
wing, generating lift. Most wings used in aviation, like those on airplanes, are
asymmetrical airfoils.
3. Clark Y Airfoil: The Clark Y airfoil is a commonly used symmetrical airfoil with
a flat bottom surface and a curved upper surface. It is often used in general aviation
and light aircraft due to its stable and predictable aerodynamic characteristics.
4. NACA Airfoil: The National Advisory Committee for Aeronautics (NACA)
developed a series of airfoil shapes with specific characteristics. NACA airfoils are
identified by a numerical code indicating the design parameters. For example, the
NACA 2412 airfoil has a camber of 2%, located 40% of the chord from the leading
edge.

5
 5. Supercritical Airfoil: The supercritical airfoil is designed to delay the onset of sock
waves and reduce drag at high subsonic speeds. It features a flattened upper surface,
and it's often used in high-speed transport aircraft.
6. Eppler Airfoil: Developed by German aerodynamicist Richard Eppler, Eppler
airfoils are a series of airfoil shapes known for their low drag characteristics. They
are often used in sailplane (glider) design.
7. Selig Airfoil: Selig airfoils are a series of airfoil shapes developed by Dr. Michael
Selig. These airfoils are commonly used in experimental and light aircraft, offering
a range of characteristics suitable for various applications.
8. Symmetrical Tapered Airfoil: A symmetrical tapered airfoil combines the features
of a symmetrical airfoil with a tapered wing planform. This design is often used in
high-performance aircraft, providing good aerodynamic characteristics over a wide
range of angles of attack.
9. Elliptical Airfoil: An elliptical airfoil is shaped like an ellipse and is theoretically
the most aerodynamically efficient in terms of lift distribution. However, achieving
a true elliptical shape in practice can be challenging.
10. Blended Winglet Airfoil: Blended winglets are not traditional airfoils but are worth
mentioning. They are wingtip extensions designed to reduce induced drag by
redistributing the wingtip vortices. Blended winglets often feature a smoothly
blended shape that improves aerodynamic efficiency.

These are just a few examples of the many airfoils used in aviation and aerodynamics.
The selection of an airfoil depends on the specific requirements of the aircraft and its
intended application. Engineers consider factors such as lift, drag, stability, and
control to choose the most suitable airfoil for a particular design.

1.7 TYPES OF WINGS:

There are several types of wings used in aircraft design, each with its own set of
advantages and disadvantages. The choice of wing type depends on the intended purpose
of the aircraft and the desired performance characteristics. Here are some common types of
wings:

6
 Fig 3: Different Types of Wings

1. Rectangular Wing:- The rectangular wing is a simple and straightforward design

with straight leading and trailing edges. While it is easy to manufacture and provides
good lift distribution, it tends to produce higher drag compared to more complex
wing shapes.
2. Tapered Wing:- The tapered wing has a geometrically decreasing chord (width)
from the wing root to the wingtip. This design reduces induced drag and can
improve the overall aerodynamic efficiency of the wing.
3. Swept Wing:-Swept wings have a backward angle along the leading edge. This
design is often used in high-speed aircraft to delay the onset of shock waves and
reduce drag at high Mach numbers. Swept wings are common in supersonic and jet
aircraft.
4. Elliptical Wing:- The elliptical wing shape minimizes induced drag and is
theoretically the most efficient in terms of lift distribution. It was famously used in
the Supermarine Spitfire during World War II. However, achieving a true elliptical
wing in practice can be challenging.
5. Delta Wing:- The delta wing has a triangular shape and is commonly used in high-
speed and high-altitude aircraft. Delta wings provide good performance at high
angles of attack and are often seen in supersonic and hypersonic aircraft.

7
 6. Variable Sweep Wing:- Variable sweep wings, also known as swing wings, can
change their sweep angle in flight. This feature allows aircraft to optimize their
wing configuration for different flight regimes, such as low-speed takeoff and
landing or high-speed cruise. The F-14 Tomcat is an example of an aircraft with
variable sweep wings.
7. Biplane:- A biplane consists of two sets of wings, one above the other, connected
by struts and wires. Biplanes were common in early aviation but have largely been
replaced by monoplanes due to increased drag. They are still used in some
specialized applications.
8. Triplane:- A triplane has three sets of wings, arranged one above the other.
Triplanes were used in some historical aircraft, notably during World War I. They
provide increased lift but are less common in modern aviation.
9. Swept-Back Wings:- Swept-back wings have a backward angle, but less extreme
than true swept wings. This design is often used in subsonic and transonic aircraft
to improve stability and control.
10. Forward Swept Wing:- In contrast to swept-back wings, forward-swept wings
have a forward angle. This design has been explored for its potential structural and
aerodynamic benefits, but it is less common due to challenges in structural design.

The choice of wing type depends on various factors, including the intended use of the
aircraft, speed requirements, and desired flight characteristics. Engineers carefully
consider these factors to design wings that optimize lift, drag, stability, and control for
a particular application.

1.8 TYPES OF WING LOCATIONS

It appears that there might be a small type in your question, and you might be
referring to "wing locations." If you mean the placement or positioning of wings on an
aircraft, I can provide information on different wing configurations and their applications:

8
 Fig 4:Types of Wing Locations

1. High-Wing Configuration:- Wings are mounted on the upper part of the fuselage.
This configuration provides better visibility from the cockpit, facilitates easier
loading and unloading of cargo or passengers, and can offer good stability.
2. Low-Wing Configuration:- Wings are mounted on the lower part of the fuselage.
This configuration can provide better aerodynamic efficiency, especially at higher
speeds, and is often seen in high-performance and military aircraft.
3. Mid-Wing Configuration:- Wings are mounted at the midpoint of the fuselage.
This configuration is less common but can provide a balance between the
characteristics of high-wing and low-wing designs.

The choice of wing configuration depends on various factors such as the aircraft's
intended purpose, speed requirements, maneuverability needs, and design considerations.
Different configurations offer different advantages and trade-offs, and engineers carefully
select the configuration that best suits the aircraft's mission profile.

1.9 LIFT THEORY

1. Definition :-Lift is the force that enables an aircraft to rise off the ground. It is
generated by the wings of the aircraft as they move through the air.
2. Bernoulli's Principle:- One common explanation for lift is based on Bernoulli's
principle. According to this principle, as the speed of a fluid (such as air) increases,
its pressure decreases. When an aircraft's wing moves through the air, the shape of
the wing causes the air above it to move faster than the air below it, creating a
pressure difference and resulting in lift.

9
 3. Wing Shape:- The shape of the wing is crucial for generating lift. Wings are
designed with an airfoil shape, typically curved on the top and flatter on the bottom.
This shape enhances the pressure difference between the upper and lower surfaces,
contributing to lift.
4. Angle of Attack:- The angle at which the wing meets the oncoming air, known as
the angle of attack, also influences lift. Increasing the angle of attack can increase
lift up to a certain point, after which the flow of air may become turbulent, and lift
decreases.
5. Other Factors:- Factors like air density, wing area, and airspeed also play a role
in lift generation. Higher airspeed and lower air density generally lead to increased
lift.

1.10 WHAT IS LIFT AND DRAG

Fig 5:Lift and Drag

1. Lift:- Lift is the force that directly opposes the weight of an airplane and holds the
airplane in the air. Lift is generated by every part of the airplane, but most of the lift
on a normal airliner is generated by the wings. Lift is a mechanical aerodynamic
force produced by the motion of the airplane through the air.

2. Drag:- Drag is the aerodynamic force that opposes an aircraft’s motion through the
air. Drag is generated by every part of the airplane (even the engines!).

10
 CHAPTER 2

LITERATURE REVIEW
The study of wing location and its impact on the aerodynamic performance of
airplanes is a multifaceted field that has garnered extensive attention from researchers and
engineers.

The positioning of wings relative to the fuselage plays a pivotal role in determining
crucial aerodynamic factors such as lift, drag, stability, and maneuverability. Research by
Torenbeek and Wittenberg (2009) [1] has explored the effects of wing sweep, emphasizing
how the sweep angle influences lift and drag distribution. Phillips (2013) [2] and Raymer
(2012) [3] have delved into the intricate aerodynamic interactions at the wing-fuselage
junction, shedding light on drag and lift characteristics.

High-lift devices, investigated by McLean and Anderson (2010)[4], are integral

components influencing takeoff and landing performance in conjunction with wing
location. Studies by Etkin and Reid (1996) [5] and Stinton delve into stability and
maneuverability considerations, crucial for an aircraft's operational effectiveness. The
empirical work of Roskam (2006) [6] and computational analyses by Dommasch et al. offer
practical insights into diverse wing configurations.

For aircraft operating in transonic and supersonic regimes, Dowell and Hayes
provide valuable considerations. Moreover, Sobester and Forrester discuss optimization
techniques for determining optimal wing locations. Cutting-edge research by Barlow and
Rae (1997) [7] and Mark Drela (2014) [8] explores innovative wing designs, showcasing
the continuous quest for improved aerodynamic efficiency.

Experimental studies conducted by AIAA and NASA contribute essential data,

while comprehensive reviews by Ojalvo and Katz and Plotkin offer synthesized
perspectives on the historical development and current state of research in this dynamic
field. Overall, the literature reflects a comprehensive exploration of the intricate
relationship between wing location and the aerodynamic performance of airplanes, shaping
the ongoing evolution of aircraft design and technology.

11
 Okamoto, M.; Azuma, A.: Aerodynamic characteristics at low reynolds numbers for
wings of various planforms. AIAAJ. (2006) [9]. Jacobs, E.; Ward, K.; Pinkerton, R.: The
characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel.
In: National Advisory Committee for Aeronautics, (1933) [10].

12
 CHAPTER 3

DESIGN AND ANALYSIS OF AIRFOIL

3.1 AIRFOIL AND TYPES OF AIRFOIL
Airfoils, also known as aerofoils, are the cross-sectional shapes of wings, blades, or
other surfaces designed to provide lift when moving through a fluid, such as air. There are
various types of airfoils, each with unique characteristics suited for specific applications.
Here are some common types of airfoils:

1. Symmetrical Airfoil

2. Asymmetrical Airfoil or Cambered Airfoil

3. Clark Y Airfoil

4. NACA Airfoil

5. Supercritical Airfoil

6. Eppler Airfoil

7. Selig Airfoil

8. Symmetrical Tapered Airfoil

9. Elliptical Airfoil

10. Blended Winglet Airfoil

3.2 DESIGNING OF AIRFOIL

Make sure you have XFLR5 installed on your computer. You can download it from
the official website. After Installation open the software click on the file option and click
create new project and name as new project. After that click the module option and click
on direct foil design. Click on foil in that click on NACA Foils. Enter the any 4 digit number
that is the one foil here we take NACA 0012, NACA 0025, NACA 2412 And N10 foils.
This is the process to design the Airfoil.

13
 Fig 6: The Figure shows different airfoils designed in XFLR5

The above figure shows the different types of Airfoils like NACA 0012, NACA
0025, NACA 2412 And N10 foils. This Airfoils are designed in XFLR5 software.

3.3 ANALYSIS OF AIRFOIL

After designing of airfoil click on module after click on XFoil Direct Analysis.
After that click on each airfoil which we designed after that click on analysis after that click
on define an analysis Reynolds number will automatically defined or you calculate the
Reynolds number enter the number and click on ok after that click on analyze. Then you
will get one foil analysis after click ok another foil repeat the same process. After that select
another repeat the same process do all foils like this then we will get a graphs as shown in
below figure. That figure shows the comparison between the foils or analysis of the foils.

14
 Fig 7: The Figure shows different airfoils Analysis in XFLR5

Airfoil analysis focuses on studying the aerodynamic properties of wing or blade

shapes. It involves analyzing geometry, lift and drag coefficients, angle of attack effects,
flow characteristics, and using simulations/testing to optimize designs for aircraft
performance. This process is crucial for enhancing aerodynamic performance and ensuring
the effectiveness of aircraft wings and propeller blades.

15
 CHAPTER 4

DESIGN AND ANALYSIS OF WING LOCATIONS

4.1 WING LOCATIONS AND TYPES OF WING
LOCATIONS
It appears that there might be a small type in your question, and you might be
referring to "wing locations." Wing locations is also known as wing Configuration. If you
mean the placement or positioning of wings on an aircraft, I can provide information on
different wing configurations and their applications:

1) High-Wing Configuration
2) Mid-Wing Configuration
3) Low-Wing Configuration

4.2 DESIGNING OF WING LOCATIONS

After designing of airfoils go to modulus and click on Wing and Plane Design. Click
on the plane option enter plane name as high wing and untick the Elevator and Fin and tick
the body option later go to main wing and click define option. Arrange chord 2 columns are
equal and offset also 2 columns are equal Then we get the rectangular wing. Click on the
save button. Keep X= -0.040 and Z= 0.020 and click on save.

Click on Plane option Click on new plane name as Mid wing untick the Elevator
and Fin and tick the body option later go to main wing and click define option. Arrange
chord 2 columns are equal and offset also 2 columns are equal Then we get the rectangular
wing. Click on the save button. Keep X= -0.040 and Z= 0.000 and click on save.

Click on Plane option Click on new plane name as Low wing untick the Elevator
and Fin and tick the body option later go to main wing and click define option. Arrange
chord 2 columns are equal and offset also 2 columns are equal Then we get the rectangular
wing. Click on the save button. Keep X= -0.040 and Z= -0.035

Input Perameters:

In this analysis we will take Reynolds numbers is 266803 we will find the Air foil
analysis after that we have to arrange wing locations.

16
 High wing Mid wing Low wing
Configuration Configuration Configuration
X- Axis -0.040 -0.040 -0.040
Z- Axis 0.020 0.000 -0.035

Fig 8.1: The Figure shows wing at above Y-Axis

In the above figure the wings we are seeing above the Y-Axis. That means

Fig 8.2: The Figure shows wing on Y-Axis

17
 Fig 8.3: The Figure shows wing at below Y-Axis

4.3 ANALYSIS OF WING LOCATIONS

After Designing of wing locations go to click on High wing after that click on
Analysis in that click on Define a New analysis. A small box is open in that go to analysis
option untick the viscous then click on the save option. Then click on Analyze option.
Repeat the same process for the Mid wing and Low wing Then we get analysis of the wing
locations.

Fig 9: The Figure shows Analysis of wing at different locations

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 CHAPTER 5

TESTING METHODS, PROCEDUCER AND WING

LOCATIONS REPORT
5.1 TESTING METHODS
Testing Methods are used to test the Aircraft models, Wing location variations etc.

When conducting a study on the effects of wing location on the aerodynamic

performance of an airplane, it's essential to follow a systematic approach. Here's a general
outline of testing methods you might consider:

1. Clearly define the objectives of your study. What specific aspects of aerodynamic
performance are you investigating?

2. Choose a specific airplane model or design for your study. Ensure that it represents
a realistic and relevant scenario.

3. Determine different wing locations to test. This may include variations in wing
sweep, dihedral, anhedral, and span.

4. Ensure that changes in wing location are incremental and systematic.

5. Ensure the scale model of the aircraft is accurate and representative.

This all are check well while doing the testing of wing locations and aircraft models.
Our project on wing locations so we have some testing methods.

Studying the effects of wing location on the aerodynamic performance of an

airplane involves a combination of theoretical analysis, computational simulations, and
experimental testing. Here are some testing methods that you can consider:

1. Wind Tunnel Testing:

 Use a wind tunnel to simulate airflow over the airplane model.

 Vary the wing locations and measure lift, drag, and other relevant
aerodynamic parameters.

 Wind tunnel testing allows for controlled conditions and precise

measurements.

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2. Computational Fluid Dynamics (CFD):

 Use computer simulations to model the aerodynamics of the airplane with

different wing locations.

 CFD allows for a detailed analysis of airflow patterns, pressure distribution,

and forces acting on the aircraft.

 This method can be cost-effective and efficient for exploring a wide range
of design variations.

3. Flight Testing:

 Conduct actual flight tests with a prototype or scaled model of the airplane.

 Instrument the aircraft with sensors to measure key parameters during flight,
such as airspeed, altitude, and attitude.

 Analyze the flight data to understand the impact of wing location on

performance.

4. Pressure Measurement Techniques:

 Install pressure sensors on the wings to measure the distribution of air

pressure.

 Pressure taps, pressure belts, or pressure-sensitive paint can provide

valuable data for assessing aerodynamic performance.

5. Force and Moment Measurements:

 Use strain gauges, load cells, or other force measurement devices to quantify
the forces and moments acting on the wings.

 This provides information on lift, drag, and stability characteristics.

6. Model Scalling:

 Consider using scaled models in wind tunnel testing or flight testing to

reduce costs and logistical challenges.

 Properly scaled models can provide relevant aerodynamic data for the full-
scale aircraft.

7. Parametric Studies:

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  Systematically vary the wing location parameters, such as sweep, dihedral,
and position relative to the fuselage.

 Analyze the data to identify trends and optimal configurations.

8. Sensitivity Analysis:

 Assess the sensitivity of aerodynamic performance to changes in wing

location.

 Identify critical design parameters that significantly affect the aircraft's

performance.

9. Comparison with Existing Data:

 Compare your results with existing data or literature on similar

configurations to validate your findings.

It's crucial to integrate findings from different testing methods to gain a

comprehensive understanding of the aerodynamic performance with varying wing
locations. Additionally, collaboration with experts in aerodynamics and aircraft design can
enhance the quality and validity of the study.

5.2 EXPERIMENTAL PROCEDURE

Our aim is to find the lift and drag at Different wing locations. To find the lift and drag
the below procedure we have to follow:
1. Open xflr5 > Module > Direct foil design.

2. Foil > NACA Foil > Enter digit 0012 > ok > ok.

3. Foil > NACA Foil > Enter digit 0025 > ok > ok.

4. Foil > NACA Foil > Enter digit 2412 > ok > ok.

5. Open file > Select n10 > open.

6. Click on Module > select Xfoil Direct analysis.

7. Click on n10 > Analysis > Define an analysis > ok > Analyze.

8. Click on NACA0012 > Analysis > Define an analysis > ok > Analyze.

9. Click on NACA0025 > Analysis > Define an analysis > ok > Analyze.

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10. Click on NACA2412 > Analysis > Define an analysis > ok > Analyze.

11. Click on Module > select Wing and Plain design.

12. Plain > Define a new plane > name as Mid wing > Untick the Elevator and
Fin > Tick the Body > In main wing click define > select any foil in 1 st row
> select the same foil in 2 nd row same as 1st row.

13. Change the wing shape by using the offset and chord > suppose we are
taking rectangular wing > keep the row 1 and row 2 offset are equal and row
1 and row 2 chord are equal and click on save option > save.

14. Click on high wing > Analysis > define an Analysis > Analysis > untick the
viscous > save > Analyze.

15. Plain > Define a new plane > name as High wing > Untick the Elevator and
Fin > Tick the Body > In main wing click define > select any foil in 1 st row
> select the same foil in 2 nd row same as 1st row.

16. Change the wing shape to rectangle > save > in main wing keep X = -0.040
and Z = 0.020 > save > ok.

17. Click on High wing > Analysis > Define an Analysis > Analysis > untick
the viscous > save > Analyze.

18. Plain > Define a new plane > name as Low wing > Untick the Elevator and
Fin > Tick the Body > In main wing click define > select any foil in 1st row
> select the same foil in 2 nd row same as 1st row.

19. Change the wing shape to rectangle > save > in main wing keep X = -0.040
and Z = -0.035 > save > ok.

20. Click on Low wing > Analysis > Define an Analysis > Analysis > Untick
the viscous > save > Analyze.

21. After analyze we get graphs compare that graphs and wing at which location
the lift is more.

22. Repeat the same process for Swept Back Wing and Delta Wing and also
compare their graphs.

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5.3 DIFFERENT WING LOCATIONS REPORT
We done a report on different types of wings in different types of locations that
report images are given below.
Rectangle Wing:

Fig 10.1: Airfoil Analysis

Airfoil analysis focuses on studying the aerodynamic properties of wing or blade

shapes. It involves analyzing geometry, lift and drag coefficients, angle of attack effects,
flow characteristics, and using simulations/testing to optimize designs for aircraft
performance. This process is crucial for enhancing aerodynamic performance and ensuring
the effectiveness of aircraft wings and propeller blades.

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 Fig 10.2: The figure shows High-Wing Configuration in Rectangular wing

A high wing configuration with a rectangular wing offers stability, increased

payload capacity, better visibility for passengers, shorter landing gear requirements, and
easier maintenance access. This design is commonly chosen for its balanced advantages,
making it suitable for various aircraft types like commercial airliners, cargo planes, and
general aviation aircraft.

Fig 10.3: The figure shows Mid-Wing Configuration in Rectangular wing

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 A mid-wing configuration with a rectangular wing strikes a balance between
aerodynamic performance and structural considerations. It offers good stability, payload
flexibility, and aerodynamic efficiency across various flight conditions, making it a popular
choice for modern aircraft in commercial, business, and military applications.

Fig 10.4: The figure shows Low-Wing Configuration in Rectangular wing

In a low wing configuration with a rectangular wing, the wings are attached closer
to the bottom of the fuselage. This design offers good aerodynamic efficiency, stability, and
improved ground visibility for pilots during takeoff and landing. It requires robust wing-
to-fuselage attachments and has specific ground handling considerations.

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 Fig 10.5: The figure shows comparison between High, Mid, Low wings
Configuration in Rectangular wing

High wing configuration places wings on top, offering good visibility and stability,
ideal for light aircraft. Mid wing is a compromise, balancing visibility, stability, and
performance, common in fighter jets and business planes. Low wing has wings beneath the
fuselage, enhancing ground visibility, maneuverability, and efficiency, often seen in
airliners and sport aircraft. Each configuration suits different needs based on visibility,
stability, and aerodynamic factors.

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Sweptback Wing:

Fig 11.1: The figure shows High-Wing Configuration in Sweptback Wing

In a high wing configuration with swept-back wings, the wings are mounted on the
upper fuselage and angled backward. This design boosts aerodynamic efficiency, stability,
and payload capacity. Passengers enjoy clear views, and the high placement provides ample
ground clearance for engines and landing gear.

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 Fig 11.2: The figure shows Mid-Wing Configuration in Sweptback Wing

In a mid-wing configuration with swept-back wings, the wings are positioned

midway on the fuselage with an angled design towards the wingtips. This setup balances
aerodynamic efficiency and stability, making it a popular choice for modern aircraft. It
offers versatility in payload capacity, sufficient ground clearance, and a sleek appearance,
contributing to its widespread adoption in various aircraft designs.

Fig 11.3: The figure shows Low-Wing Configuration in Sweptback wing

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 In a low wing configuration with swept-back wings, the wings are mounted closer
to the bottom of the fuselage and angled backward toward the wingtips. This design
enhances aerodynamic efficiency and stability, especially at high speeds. Low-wing
configurations with swept-back wings are commonly seen in modern jet aircraft, providing
a sleek appearance and optimal performance characteristics for faster flight and improved
handling.

Fig 11.4: The figure shows comparison between High, Mid, Low wings in
Sweptback wing
High wing configuration: Positioned on top of the fuselage, offers stability and good
visibility, suitable for transport aircraft.

Mid wing configuration: Placed midway on the fuselage, balances efficiency and
stability, versatile for various aircraft types.

Low wing configuration: Mounted close to the bottom of the fuselage, enhances
aerodynamic efficiency and is common in modern jet aircraft.

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Delta Wing:

Fig 12.1: The figure shows High-Wing Configuration in Delta Wing

In a high wing configuration with a delta wing, the wings are mounted on top of the
fuselage in a triangular shape resembling the Greek letter delta. This design, commonly
found in military fighter jets, offers exceptional maneuverability, efficient supersonic flight,
space efficiency, stability, and reduced landing speeds.

30
 Fig 12.2: The figure shows Mid-Wing Configuration in Delta Wing

In a mid-wing configuration with a delta wing, the wings are positioned at the
midpoint of the fuselage in a triangular shape resembling the Greek letter delta. This design
balances aerodynamic efficiency, stability, and maneuverability, making it suitable for
various high-performance aircraft, including military fighters and experimental aircraft.
The mid-wing placement ensures good handling characteristics and allows for optimal
integration of internal systems and fuel tanks while maintaining a compact overall design.

31
 Fig 12.3: The figure shows Low-Wing Configuration in Delta wing

In a low wing configuration with a delta wing, the wings are mounted closer to the
bottom of the fuselage in a triangular shape resembling the Greek letter delta. This design
enhances aerodynamic efficiency, especially at high speeds, making it ideal for high-
performance aircraft such as fighter jets and supersonic aircraft. The low-wing placement
contributes to stability and maneuverability while allowing for effective integration of
internal systems and weapons. This configuration is often chosen for its sleek appearance
and superior performance characteristics in fast and agile flight scenarios.

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Fig 11.4: The figure shows comparison between High, Mid, Low wings in Delta wing

High Wing Configuration with Delta Wing:

 Positioned on top of the fuselage, offering stability and visibility.
 Ideal for military aircraft requiring high maneuverability and supersonic flight.
 May have challenge in ground handling due to high wing placement.

Mid Wing Configuration with Delta Wing:

 Placed midway on the fuselage, balancing efficiency and maneuverability.

 Common in high-performance aircraft, providing good handling and internal
space.

Low Wing Configuration with Delta Wing:

 Mounted close to the fuselage bottom, enhancing aerodynamic efficiency.

 Suitable for high-performance fighter jets and supersonic aircraft.
 Requires careful design for ground clearance and structural integrity.

The above graphical figures shows the different types in different locations. The
graph shows at what location the Airplane reaches maximum. This is the detailed report on
different wing locations on Airplane.

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Result Values:

Case-1: Rectangular Wing.

Hing wing Mid wing Low wing

Configuration Configuration Configuration
X-Axis (Lift) 6 1.8 2.6
Y-Axis (Drag) 3.8 2 1.8

We will check the above table at High wing configuration we will get more Lift
with less Drag.

Case-2: Swept Back Wing.

Hing wing Mid wing Low wing

Configuration Configuration Configuration
X-Axis (Lift) 1.2 1 1
Y-Axis (Drag) 1.4 1 0.8

We will check the above table at Low wing configuration we will get more Lift with
less Drag.

Case-3: Delta Wing.

Hing wing Mid wing Low wing

Configuration Configuration Configuration
X-Axis (Lift) 1 1 1.4
Y-Axis (Drag) 0.8 0.6 1.8

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 CHAPTER 8
CONCLUSION
The study of wing location in relation to the aerodynamic performance of an
airplane is a critical and complex aspect of aircraft design. The position of the wings
significantly influences the overall aerodynamic characteristics, affecting key parameters
such as lift, drag, stability, and maneuverability. Through systematic investigation and
analysis, researchers and engineers can gain valuable insights into the optimal wing
placement for different types of aircraft and missions.

The findings of such studies contribute to the enhancement of aircraft efficiency,

safety, and performance. By understanding how wing location impacts aerodynamics,
designers can make informed decisions to achieve a balance between lift and drag, ensuring
optimal fuel efficiency and maneuvering capabilities. Additionally, considerations for
stability and control become crucial elements in determining the most suitable wing
position for specific applications.

As technology advances and computational tools improve, researchers can conduct

more sophisticated simulations and experiments, leading to further refinements in aircraft
design. The continuous exploration of wing location's impact on aerodynamic performance
is vital for the ongoing development of innovative and efficient aircraft, contributing to the
evolution of aviation and aeronautical engineering.

If it observed that lift is more in rectangular wing at High wing configuration. i.e.,
lift of 6N and drag of 3.8N is Observed.

If it observed that lift is more in swept back wing at Low wing configuration. i.e.,
lift of 1N and drag of 0.8N is Observed.

If it observed that lift is more in delta wing at Mid wing configuration. i.e., lift of
1N and drag of 0.6N is Observed.

35
 CHAPTER 9

REFERENCE
1. E. Torenbeek and H. Wittenberg, “Flight Physics”, Spinger link Publications,
2009.
2. Dr. Anna C. Phillips, “Perceived Stress”, Spinger link Publications, 2013.
3. Daniel P. Raymer, “Aircraft Design: A Conceptual Approach”, American Institute
of Aeronautics and Astronautics, 2012.
4. Claire Anderson, “Presenting and Evaluating qualitative Research”, American
Journal of Pharmaceutical Education, 2010.
5. Bernard Etkin, Lloyd Duff Reid, “Dynamics of Flight: Stability and control”, 3rd
Edition, published by Wiley, 1996.
6. J. Roskam, “Flight Dynamics of Rigid and Elastic Airplanes”, eBook
Publications, 2006.
7. Jewel B. Barlow, William H. Rae, “Low-Speed Wind Tunnel Testing”, 3rd
Edition, ISBN Publications, 1997.
8. Mark Drela, “Flight Vehicle Aerodynamics”, MIT Press Publications, 2014.
9. Okamoto, M.; Azuma, A.: Aerodynamic characteristics at low reynolds numbers
for wings of various planforms. AIAA J. 49(6), 2011.
10. Jacobs, E.; Ward, K.; Pinkerton, R.: The characteristics of 78 related airfoil
sections from tests in the variable-density wind tunnel. In: National Advisory
Committee for Aeronautics, 1933.

36
 CHAPTER 10

GROUP PHOTOS

37