Unmanned Aerial Vehicle (UAV) is an important technology for military and security application. Various missions can be done using UAV such as surveillance in unknown areas, forestry conservation, and spying enemy territory. Selection of components such as aerofoil plays huge roll in performers of UAV in terms of lift, drag, load carrying capacity, range etc. This project presents an approach for designing of wing by selecting proper aerofoil and CFD analysis for verifying aerodynamics characteristics.

1. Presented By:
Pranit Dhole

2. • Abstract
• Introduction
• Aim
• Objectives
• Basics of aerodynamics
• Selection of aerofoil
• CFD simulations of NACA aerofoils
• Results Comparison
• Wing Tip Vortices
• Winglet Design

3. • Unmanned Aerial Vehicle (UAV) is an important technology for military and security
application. Various missions can be done using UAV such as surveillance in unknown
areas, forestry conservation, and spying enemy territory
• Selection of components such as aerofoil plays huge roll in performers of UAV in terms of
lift, drag, load carrying capacity, range etc.
• This project presents an approach for designing of wing by selecting proper aerofoil and
CFD analysis for verifying aerodynamics characteristics.

4. Sr.
No.
Author Published Journal Objective of Literature Conclusion
1. Kadir Alpaslan
Demir, Halil
Cicibas et. al.
Defence Science
Journal, Vol. 65, No.
July 2015
Objective of this paper is
to provide new domain
for research in UAVs for
new researchers. This
paper provides basic
information of UAVs,
types, Technology,
Operation, Standard and
Certification.
In this study, an outline of basic
research areas in the UAV domain is
presented. The intended audience is
the researchers new to the domain.
With this study, new researchers will
be able to quickly overview the main
research areas and choose an
appropriate area that interests them
2. PRASETYO EDI,
NUKMAN
YUSOFF and
AZNIJAR
AHMAD YAZID
WSEAS
TRANSACTIONS on
APPLIED and
THEORETICAL
MECHANICS
Journals
This paper intends to
presents the design
improvement of airfoil for
flying wing UAV
The Author can conclude that a
Ne334 with 13.5% thickness is a
better design that surpass it original
airfoil geometric of Eppler 334 hence
this new airfoil can be use for the
building of low Reynolds number
Flying Wing Unmanned Aerial
The Author found that XFOIL
is only valid up to a certain range of

5. Sr.
No.
Author
Published
Journal/Conference
Objective of Literature Conclusion
3. Adam Dáugosz1,a)
and Wiktor
Klimek2,
AIP Conference
Proceedings (2018)
The aim of the
optimization is to improve
strength and stiffness
together with reduction of
the weight of the
structure.
The paper presents the
evolutionary multi-objective
optimization of the UAV wing
structure. Numerical FEM model,
consisting of different composite
materials is created. Adequacy of
the numerical model is verified by
results obtained from the
experiment, performed on a
tensile testing machine.

6. • In modern day warfare one of the most discussed
technological weapon lately has been the UAV.
• Unmanned Aerial Vehicle as an aircraft without a
human pilot on board.
• India Army operates various UAVs like Israeli Heron,
US Predator MQ-9.
• DRDO of India is working on its own UAVs like
Rustom 2, AURA UCAV, ADE Nishant.

8. • The problem of optimal design of the aircraft wing has been considered by many researchers.
• It concerns passenger or military aircraft and Unmanned Aerial Vehicle (UAV) as well.
• Design process of the aircraft wing have to take several goals and restrictions into consideration.
• The aerofoils should be characterized by: high lifting force, low aerodynamics drag, low mass, high
endurance, etc.
• Consideration of more than one criterion leads to the multi-objective optimization.
• This Project aims to design wing for UAVs by optimization of aerodynamics and structural
characteristics.

9. To Design and Analyze the wing for unmanned aerial vehicle.
• To Selection of proper Aerofoil
• To design wing for Cruise Speed =35 m/s
• To design wing of Span = 400 mm
• To design wing of Chord = 80 mm
• To Design and analyse aerodynamics and structural characteristics using CAD,
CFD & CAE

10. Literature Survey ,
Problem Defination
Aerofoil Selection
using CFD,
Comparative
study between
Aerfoils
Structural
Analysis using
FEA
Results ,Contour
Plots, , Conclusion,
Takeaways

11. •Lift is the force component perpendicular to the
direction of relative motion.
•Drag is the force component parallel to the
direction of relative motion.
•Weight is acting downward due to gravity force.
•Thrust is force that moves aircraft forward.

13. • Airfoil is a streamline body which plays an important role in any aircraft because it has to
generate adequate amount of lift to hold the aircraft in the air with less amount of drag
• The aerofoils should be characterized by: high lifting force, low aerodynamics drag, low mass, high
endurance.

14. Following are the terms that are related to aerofoils:
•Chord: Chord is defined as the distance between the leading edge which is the point at the front of the aerofoil
and has maximum curvature and the trailing edge which is the point at the rear of the aerofoil with maximum
curvature along the chord line.
•Chord line: Chord line is defined as the straight line connecting the leading and trailing edges.
•Upper surface: Upper surface is also known as suction surface which is associated with high velocity and low
static pressure.
•Lower surface: Lower surface is also known as pressure surface with higher static pressure.
•Angle of attack (AOA): The angle formed between a reference line on a body and the oncoming flow.

15. • Chord Length (L) = 80 mm
• Inlet Velocity (V) = 35 m/s
• Α varies from 8 ̊ – 35 ̊

16. • Root Chord = 80 mm
• Tip Chord = 64 mm
• Average Chord = 74 mm
• Area of Wing = 0.028 m²
• Aspect Ratio :
Span²/Area= 0.4/0.028
= 14.28

17. To calculate lift and drag forces :
1. Lift Force : 𝟎. 𝟓 × 𝝆 × 𝑨 × 𝑽2
× 𝑪𝒍
2. Drag Force : 𝟎. 𝟓 × 𝝆 × 𝑨 × 𝑽² × 𝑪𝒅
To calculate lift and drag coefficients:
• 𝑪𝒍 =
𝟐×𝑳𝒊𝒇𝒕 𝑭𝒐𝒓𝒄𝒆
𝝆×𝑨×𝑽²
• 𝑪𝒅 =
𝟐×𝑫𝒓𝒂𝒈 𝑭𝒐𝒓𝒄𝒆
𝝆×𝑨×𝑽²

18. Problem
Identification
• Setting the
modelling ends.
• Placing the
model to
domain.
Pre Working
• Creating an
airfoil model.
• Meshing
configuration
Solver
• Numerical
Computation
• Placing the
appropriate
boundary
condition
Post Processing
• Analyzing the
results
• . Graphical
diagrams.
• Contour Details.

21. SOLIDWORKS Simulation has four options for solvers: Auto,
FFEPlus, Direct Sparse, and Large Problem Direct Sparse

22. When we mesh a model, the software generates a mixture of solid, shell, spring, and
contact elements based on the created geometry.

25. Angle of Attack (Degree) Lift Force (N) Drag Force (N) Lift to Drag Ratio
0 AOA 2.219747584 0.572310337 3.8785
8 AOA 3.401726171 0.744741445 4.5679
15 AOA 4.943257736 1.076776625 4.591
25 AOA 7.409100621 1.705407723 4.3444
30 AOA 7.563717554 1.740433201 4.3459
35 AOA 9.2794224951 2.231545766 4.15

26. 0
1
2
3
4
5
6
7
8
9
10
0 AOA 8 AOA 15 AOA 25 AOA 30 AOA 35 AOA
Forces
(N)
Angle of Attack
Angle of Attack vs Forces
Lift Force Drag Force

27. 3.4
3.6
3.8
4
4.2
4.4
4.6
4.8
0 8 15 25 30 35
Lift to Drag Ratio

28. 0
1
2
3
4
5
6
7
8
9
10
0 A-O-A 8 A-O-A 15 A-O-A 25 A-O-A 30 A-O-A 35 A-O-A
Comparison
Lift Force Drag Force

30. Angle of Attack (Degree) Lift Force (N) Drag Force (N) Lift to Drag Ratio
0 AOA 1.6588043427 0.57903575463 2.8647
8 AOA 2.868472135 0.7682922745 3.7335
15 AOA 4.5711083073 1.0910560178 4.1896
25 AOA 6.1702914680 1.6474459995 3.7453
30 AOA 7.0366753276 1.8398192954 3.8246
35 AOA 7.053802649 2.2628314129 3.1172

31. 0
1
2
3
4
5
6
7
8
0 AOA 8 AOA 15 AOA 25 AOA 30 AOA 35 AOA
Force
(N)
Angle of Attack
Angle of Attack vs Forces
Lift Force Drag Force

32. 0
0.5
1
1.5
2
2.5
3
3.5
4
4.5
0 8 15 25 30 35
Angle of Attack
Lift to Drag Ratio

33. 0
1
2
3
4
5
6
7
8
9
10
0 A-O-A 8 A-O-A 15 A-O-A 25 A-O-A 30 A-O-A 35 A-O-A
NACA 4412 vs Clark Y
NACA 4412 Clark Y

34. • When an airfoil is flown, a pressure differential
exists between the upper and lower surfaces of
the airfoil.
• The pressure above the wing is less than
atmospheric pressure and the pressure below
the wing is greater than atmospheric pressure.
• Air always moves from high pressure toward
low pressure, and the path of least resistance is
toward the airfoil’s tips
• This flow of air results in “spillage” over the tips,
thereby setting up a whirlpool of air called a
vortex.

36. • Winglets are vertical extensions of wingtips that improve
an aircraft's fuel efficiency and cruising range.
• Designed as small airfoils, winglets reduce the
aerodynamic drag associated with vortices that develop
at the wingtips as the airplane moves through the air.
• By reducing wingtip drag, fuel consumption goes down
and range is extended.

37. Angle of Attack Lift Force without winglet (N) Lift Force with winglet (N) % Increase
0 AOA 2.219747584 2.7586933319 24.27 %
8 AOA 3.401726171 5.7761425191 69.80 %
15 AOA 4.943257736 7.1172669289 44%
25 AOA 7.409100621 8.8725960593 19.75%
30 AOA 7.563717554 10.222124582 35.14%
35 AOA 9.2794224951 9.4322349479 1.64%

38. 0
2
4
6
8
10
12
0 A-O-A 8 A-O-A 15 A-O-A 25 A-O-A 30 A-O-A 35 AOA
Chart Title
Without winglet (N) With winglet (N)

39. • NACA 4412 has more lift than Clark Y aerofoil at 35 m/s speed , hence NACA 4412 is selected for UAV.
• As A-O-A increases lift force increases but it comes with extra drag force.
• NACA 4412 has good lift to drag ratio between 0 to 15 degree A-O-A, hence it is recommended to
use flaps A-O-A up to 15 degree.
• NACA 4412 has best Lift to Drag ratio at 15 Degree A-O-A creating maximum Lift force of
= 7.1172 (N) × 2
= 14.3 (N)
= 1.5 Kg Weight Lifting capacity

40. • Simulation with completely built UAV model with both wings in action.
• Structural analysis of Wing.