Flying Wing UAV Project Report

Faisal, shoaib, samiullah, Ahmed, habib, qayum 1|P a g e Projectimplementation
Group members
1. Habib Ahmed
2. FaisalEhsan
3. Abdul Qayum
4. Shoaib Zafar
5. SamiullahNaseem
6. Ahmed Ali
Instructor:Mr.Islam Zaki
Course-HND-AE Sept13
Subject:ProjectImplementation

Table of content
Sr. No Topic
Page
Number
1 Abstract & Aim 3
2 Introduction 4-6
3 Design 7-8
4 AutoCAD 9-13
5 Gantt chart 14-17
6 Budget 18-19
7 Task distribution 20
8 Electronics installation 22-24
9 Calculations 25-30
10 Construction 32-38
11 Airfoil selection 40-46
12 Trouble shooting 48-50
13 Safety precautions 51
14 Conclusion 52
15 Appendix 53
16 Proposal (parametric study 1) 54-55

19 Proposal Report 61
20 Evidences 62-63
21 Tools for construction 64-66
22 Material/component used 67-68
23 Weight (actual & estimation) 70-71
24 Testing 72-74
26 References 75-76

ABSTRACT& AIM
This project presents a flying wing design which has weight of about 1kg. The basic
idea of the project is to design and construct a working flying wing which would be
used for surveillance, military applications and other scientific researches in its most
economical way of frequent flight. The project comprises of three basic stages which
includes designing a concept and then aerodynamic analysis of concept and after
this manufacturing of the concept.

INTRODUCTION
In this project we are going to construct a UAV with some certain parameters as
asked by our instructor in the proposal. UAV stands for unmanned aerial vehicle.
These include drones and other unpiloted aerial vehicles which are controlled by
remotes from the ground. These UAV’s are divided into two sub groups Autonomous
aircrafts and remotely piloted aircrafts. The UAV’s are the powered aerial vehicles
that does not carry a human operator but uses all the aerodynamic forces the lift the
vehicles and perform different manoeuvring stunts. There are many different names
of these kinds of aircrafts for example UAV’s or RPAS or model aircraft but it is
majorly known as drones.
If we speak about history of UAV’s so in mid of 18th century Austria sent
unmanned bomb-filled balloons to attack Venice. But the kinds of drones we see
today were invented during early 19th century and were actually used for target
practice to train the military people. It became extremely useful during World War 1
when pilotless aerial torpedo were introduces for dropping off the explosives. The
same story was repeated in World War 2 but this time the UAV’s were much
advanced in terms of technology and accuracy. We are assigned a project for this
semester and we’ve decided to construct a UAV. We have decided to work on fixed
wing FPV skyVU-10 which will be used for surveillance and other transportation
purposes. Apart from this we are also assigned to research other parametric studies
regarding UAV’s so we decided to choose mini Guinea and pool noodle as our other
options which we are going to detail in discuss in the report ahead.All these UAV’s
have different uses and applications. All of them have some advantages over the
other with addition of some disadvantages as-well.
In this report we are going to discuss detail constructional steps which we are
going to take in building up this project. We are going to mention all the research
work done on this UAV to construct it plus we are also going to mention the
difficulties faced while accomplishing this research and how we faced with those
difficulties and came up with a solution. We are going to construct the UAV by the
help of some online resources but with some effective changes. In this assignment
we are going to assign each group member their specific tasks and at the end of the
day we are going to compile all that research work and form a report which we
expect to be approved by our instructor. We are going to add up a Gantt chart at the

end of the report which will be renewed every week if required. In that Gantt chart we
are going to include all the information which will help the constructor to understand
our planning and mindset in a much better way.
FLYING WING RC PLANE
A flying wing is fixed wing with no tail attached. It has no definite fuselage connected
and most of the part is played with the wings itself. The fuselage is just connected
between two wings connecting the wings and used for carrying the motor, battery
and other electronic equipment’s.
Fixed Wing is considered to be one of the most efficient aircraft theoretically from the
point of view its aerodynamic structure and its structural shape. The wings in this
aircraft provide stability and the control over the aircraft. It is considered to be the
most important structure of the aircraft and for successful flight test it is very
important that the wing structure is accurate and both the wings are linear in shape.
The main aim of the project is to construct and test the flying wing and carry out the
aerodynamic analysis and compare it with other surveillance aircrafts.
In the initial stages the project will start with accurate dimensions of the wing and
then calculating accurate lift to drag ratio which would lead us to the calculation of
actual center of gravity which is one important factor to be calculated. The center of
gravity of the glider would be calculated by assuming the weight of different
components with respect to their location and placing them right on the spot and
concluding the center of gravity. Center of gravity is one important factor which
should be calculated properly as it could affect the longitudinal stability of the glider.
Our calculation is very important otherwise the design would not be very effective.

History to UAVs
The market feasibility of UAV integration is paramount in determining which
applications are likely to emerge in the coming years as desirable uses of the NAS in
the public sector. As a part of the larger project performed by the EPP Project
Group, our group’s research will provided a basis for analysis by the Governance,
Risk, and Technologies and Standards. By utilizing the information provided in our
research, these groups can further apply the information to analyze airspace
restrictions, design considerations, and integration policy tailored to applications that
are viable in the near future. For example, if a feasible operation were to be
performed at an altitude of 1500 feet, this application would require more monitoring
and incident countermeasures than say, and application for localized surveillance
with operations one-hundred-fifty feet or lower in altitude. In addition, if our group is
able to produce a set of viable applications, we can emphasize these and perform
further research relative to the use of this application and potential investment
therein.
Investment in UAV technology is important for many reasons extending far beyond
market viability. One must also consider the international implications of
discontinuing UAV research. Several other countries including Japan and the UK
are currently applying UAVs for uses outside the military sector. If UAVs were to
someday require use on a regular basis, and the commercial development of UAVs
in the US is lacking, significant reliance on foreign UAV technology and importation
will become more and more necessary in order to meet the need.

DESIGN CONCEPT (INITIAL)
Figure1:Top View
Figure2:Side View
Figure3:Front View
8’’
15’’
8’’
4.2’’4.2’’
15’’
13’’
C.G
8.5’
’
13’
19’’ 10’’ 19’’
7’’
Servo (5g)
Camera (110g)
Battery (158g)
SpeedController(22G) Motor (53g) and propeller(30g)
Spar

Final Design
Figure4:Top view
Figure5:Front view
#Ref 1 #Ref 4 #Ref 3

AUTOCAD DESIGN (INITIAL)
Figure6: Frontangled View (Conceptual)
Figure7:SideView (conceptual)

Figure8:FrontView (conceptual)
Figure9:Top view (X-ray mode)

AUTOCAD UPDATED (FINAL)
Figure10:Topview(X-ray mode)
Figure11:Bottom view(Shadededgesmode)

Figure12:Angleview(shaded edges mode)
#Ref 11

Initial Ganttchart

Explanation
 In our grant chart, we planned our second week for researching in which we
as a group researched on different aircrafts and their constructional
procedures. In this week, we decided one UAV on which we are going to
make our project and planned other parametric studies which are fixed wing
FPV SKYVU-10 with two other parametric studies. In this week, we distributed
the work between group members to research on three parametric study so
that everyone is involved in the project.
 In our second week, we also intend to submit our proposal to our instructor
and after his acceptance we are going learn the calculations which is to be
performed in construction plus we will also design our UAV manually and in
software named as AUTOCAD. This whole period is illustrated in the Gantt
chart above.
 Then comes the purchasing period which is after designing & calculation. For
purchasing, the budget of material requires whole group contribution. As we
figured out our budget according to the RC plane we chose which will be
around 2000-2200AED, this cost 450 to each member of the group evenly.
 Once the calculation and design is all correct, we’ll start the construction
process in 9th week which might take4 weeks as shown above. During this
month, we will be making fuselage, wings, control surfaces, landing gear and
constructing electrical work which again might take a month maximum.
 Also during these periods, we also have other subject to study and make
assignments which is going to be in week 5 or later. Also there will be other
distractions during the construction period, so 1 months is chosen to
accomplish the plan.
 After construction, the frequency setting and tuning will be done. Once the
frequency tuning on the remote is done, we are going to test the UAV with
one person making a video of it and if any damage occurs, we are going to
utilize 4-5 days for repairing process which is specified in the Gantt chart in
week 13th. By the time we’ll end up our repairing and Re-testing process, only
1 weekis going to be left in which we are going to finalize our report. The
report will be done throughout the whole period which would include all the
details, calculations, ideas and other parameters.

Gantt chart

Gantt chartexplanation
In our Gantt chart we explained the work we have been doing on our project. It
shows what we have already completed and what we are going to complete in the
coming days. As we have moved on to 11th week of the semester and by now we
have to be at finishing moments of our constructions as we mentioned in the
previous Gantt chart that we would complete all the construction work by 12th week
so we are exactly following the same Gantt chart explanation and we are almost
done with our construction work. Within this coming week we are going to finish out
construction and test our project. After the testing is done we are going to work on
the repairing and all the trouble we faced during the testing and try to fix it as soon
as possible.
The Green color shows the work which have been completed and the yellow color
represents the colour which is to be done. Our proposal, design, research, and
AutoCAD are completely done. Purchasing and construction work is about to end
and is 80-85% completed. We started our final report work long back in the 7th week
and by now it is 50 % completed. We are going to prepare for our presentation in the
final week of the semester as we to have to go through the whole report once it is
done completely and only then we can prepare it. This is the reason why it is marked
with a red colour.
We updated our Gantt chart a-bit early as we were going a bit slow from our previous
Gantt chart what we thought. The amendments made to the Gantt chart are not
much but we have tried to follow it as much as we could. We started a bit late with
our report work but we are going to complete it on time. The rest of the things are
fine and went very well as we mentioned in the first Gantt chart.

BUDGET ESTIMATION
MATERIAL COST/AED
BATTERY 280
MOTOR 190
ESC 180
CAMERA 300
PROPELLER 30
SERVO’S 100
WIRES 30
ACCESSORIES (glue, blades, screws) 60
MATERIAL (FOAM/BALSA WOOD) 150
REMOTE CONTROLLER 400
LANDING GEAR 50
TOTAL AED 1780

ACTUAL BUDGET
MATERIAL COST/AED
BATTERY 190
MOTOR 250
ESC 170
CAMERA 150
PROPELLER 20
SERVO’S 90
WIRES 50
ACCESSORIES (glue, blades, screws) 60
MATERIAL (FOAM/BALSA WOOD) 130
REMOTE CONTROLLER 290
LANDING GEAR 95
LAMINATION SHEET 55
TOTAL AED 1560

TASK DISTRIBUTION
TASKS GROUP MEMBERS INVOLVED
PROJECT SELECTION FAISAL, SHOAIB , HABIB, SAMIULLAH
PROPOSAL FAISAL, SHOAIB , HABIB
DESIGNING, AUTOCAD FAISAL
CALCULATION SHOAIB, SAMIULLAH
AIRFOIL, MATERIAL HABIB, AHMED, QAYUM
CONSTRUCTION FAISAL, SHOAIB , HABIB, SAMIULLAH, AHMED, QAYUM
ELECTRONICS FAISAL, SHOAIB , HABIB, SAMIULLAH, AHMED, QAYUM
PURCHASING FAISAL, SHOAIB , HABIB, SAMIULLAH, AHMED, QAYUM
REPORT FAISAL, SHOAIB , HABIB, SAMIULLAH, AHMED, QAYUM
TESTING FAISAL
FINALIZING FAISAL, HABIB

ELECTRONIC SETUP & INSTALLATION
1. Brushless motor
The brushless motors has increased power to weight ratio and brushless motors
has also brought about an entire new breed of motors has also brought an entire
new type of micro RC plane.
2. Li-Po battery
Li-Po batteries is a short form for Lithium Polymer. These type of battery
rechargeable battery that had been used in RC planes, Multi-rotor and helicopter.
RC Li-Po batteries have three main things going for them that make them the perfect
battery choice for RC planes
 RC Li-Po batteries are light weight and can be made in almost any shape and
size.
 RC Li-Po batteries have large capacities, meaning they hold lots of power in a
small package.
 RC Li-Po batteries have high discharge rates to power the most demanding
electric motors.

3) ElectronicSpeed Controller.
The function of the electronic speed controller is to control the speed of RC
electric motor. The electronic is plugged into the receiver. Then both the motor
and battery plugs into the receiver. The ESC start to work as throttle stick is
moved. The receiver gives information to the ESC to change the speed of the
motor.
4) Servo
The servo are used in RC plane to move the control surface with the help of linkage
rod. It also performs many other optional functions that can be installed on the
airplane. For example it can be used in landing, aileron, flaps, camera triggers etc.
The servos come in market in various weights, speed, size and strengths.

5) Transmitter
The transmitter is the one which is used to the control the RC airplane for flying. It
has many switches and controls for moving, manoeuvring, elevators deflection,
throttle control.
6) Receiver
The receiver is an electronic unit that receives the signals from the transmitter and
send to the other component fixed to it. For example the receiver receives signals
from the transmitter and relays these signals to the servo.

Figure13: ELECTRONIC COMPONENTS CIRCUIT DIAGRAM
Motor
ESC
Battery
Receiver
Servo Servo
Mixer

Calculations
Calculating C.G (Centre Of Gravity)
𝑪. 𝑮 =
𝑪 𝑹 𝟐 + ( 𝑪 𝑹 × 𝑪 𝑻) + 𝑪 𝑻 𝟐
𝟔 × ( 𝑪 𝑹 + 𝑪 𝑻)
+
𝑺 𝑷 × [𝑪 𝑻 + ( 𝟐 × 𝑪 𝑻)]
[𝟑 × ( 𝑪 𝑹 + 𝑪 𝑻)]
𝑪. 𝑮 =
(𝟏𝟑) 𝟐
+ ( 𝟏𝟑 × 𝟖) + (𝟖) 𝟐
𝟔 × ( 𝟏𝟑 + 𝟖)
+
𝟏𝟐. 𝟔 × [𝟏𝟑 + ( 𝟐 × 𝟖)]
[𝟑 × ( 𝟏𝟑 + 𝟖)]
𝑪. 𝑮 = 𝟐. 𝟔𝟕𝟒𝟔 + 𝟓. 𝟖
𝑪. 𝑮 = 𝟖. 𝟒𝟖𝒊𝒏𝒄𝒉𝒆𝒔 = 𝟐𝟏𝟓𝒎𝒎From the nose
Figure14: C.G location with all components added
#Ref 2 #Ref 10

Calculating Drag
Total Drag = Induced Drag Coefficient+ Parasite Drag Coefficient
𝐶 𝐷𝑃 =
𝐶𝑓 × 𝑘 × 𝑆 𝑤𝑒𝑡
𝑆
Cf= Skin friction dragcoefficient
Cf=
0.445
log 𝑅𝑁 2.58
Cf=
0.445
𝑙𝑜𝑔8944.3 2.58
Cf= 0.00717
Wetted area of the wing Swet
𝑆 𝑤𝑒𝑡 = 2 × (𝑊𝑖𝑛𝑔 𝐴𝑟𝑒𝑎 ) × 1.02
𝑆 𝑤𝑒𝑡 = 2 × (2978.4) × 1.02
𝑺 𝒘𝒆𝒕 =6075.936 cm2
𝐶 𝐷𝑃 =
𝐶𝑓 × 𝑘 × 𝑆 𝑤𝑒𝑡
𝑆
𝐶 𝐷𝑃 =
0.00717 × 1.13× 6075.936
2978.4
CDP = 0.0165
CDI = Induced DragCoefficient
𝐶 𝐷𝐼 =
𝐶 𝐿2
𝜋 × 𝐴𝑅 × 𝑒
 e is assumedas 0.95, the efficiencyfactor.
𝐶 𝐷𝐼 =
1.19912
𝜋 × 4.58 × 0.95

𝑪 𝑫𝑰 = 𝟎. 𝟏𝟎𝟓𝟏
CDtotal= 0.1051 + 0.1051
CDtotal= 0.1216
𝐷𝑟𝑎𝑔 =
1
2
𝜌𝑣2
𝑆𝐶 𝐷
Dtotal=
1
2
× (1.225) × (5)2
× (0.29784) × (0.1216)
Dtotal= 0.554 N
Calculating Lift-to-Drag Ratio(
𝑳
𝑫
)
(
𝐿
𝐷
) =
𝐶𝐿
𝐶 𝐷
(
𝐿
𝐷
) =
1.1991
0.1216
(
𝑳
𝑫
) = 𝟗. 𝟖𝟔
Stall speed calculation
𝑉𝑆 = √
2𝑊
𝜌 × 𝑆 × 𝐶𝐿 𝑚𝑎𝑥
𝑉𝑆 = √
2 × (0.965)
(1.225)× (0.29784)× (1.1991)
𝑽 𝑺 = 𝟐. 𝟏 𝒎/𝒔
#Ref 10

Calculating Wing Area (S)
Wing Area (S) = Wingspan (b) × Average chord (CAV)
b= 1168mm
CAV=
𝐶 𝑅+𝐶 𝑇
2
𝐶𝐴𝑉 =
325+ 185
2
CAV = 255 mm
S = 1168 x 255
S = 297840 mm2
 0.29784 m2
Calculating Aspect Ratio (AR)
𝐴𝑅 =
(𝑤𝑖𝑛𝑔 𝑠𝑝𝑎𝑛)2
𝑊𝑖𝑛𝑔 𝐴𝑟𝑒𝑎
𝐴𝑅 =
(1168)2
297840
AR = 4.58 : 1
Calculating Reynold’s Number (RN)
𝑹𝑵 =
𝝆 × 𝑽 ×
𝑺
𝒃
𝝁
𝜗 =
𝜇
𝜌
=
1.789×10−5
1.255
= 𝟏. 𝟒𝟐𝟓𝟓 × 𝟏𝟎−𝟓
m-2s
V = Flying wing speed, which is assumed as5 m/s.
𝑅𝑁 =
𝑉 ×
𝑆
𝑏
𝜗
𝑅𝑁 =
(5) ×
(0.29784)
(1.168)
(1.4255 × 10−5)
RN= 89442.3

Calculating Wing Loading (With Landing Gears)
𝑾𝒊𝒏𝒈 𝑳𝒐𝒂𝒅𝒊𝒏𝒈 =
𝑾𝒆𝒊𝒈𝒉𝒕 𝒐𝒇 𝒕𝒉𝒆 𝒂𝒊𝒓𝒄𝒓𝒂𝒇𝒕
𝑾𝒊𝒏𝒈 𝑨𝒓𝒆𝒂 ( 𝑺)
𝑊𝑖𝑛𝑔 𝐿𝑜𝑎𝑑𝑖𝑛𝑔 =
(0.965)
(0.29784)
𝑾𝒊𝒏𝒈 𝑳𝒐𝒂𝒅𝒊𝒏𝒈 = 𝟑. 𝟐𝟒 𝒌𝒈/𝒎 𝟐
Calculating Mean Aerodynamic Chord (m.a.c)
𝑇𝑎𝑝𝑒𝑟 𝑅𝑎𝑡𝑖𝑜 (𝜎) =
𝐶 𝑇
𝐶 𝑅
𝑇𝑎𝑝𝑒𝑟 𝑅𝑎𝑡𝑖𝑜 (𝜎) =
185
325
𝑻𝒂𝒑𝒆𝒓 𝑹𝒂𝒕𝒊𝒐 ( 𝝈) = 𝟎. 𝟓𝟔𝟗 (𝒊𝒏𝒄𝒍𝒖𝒅𝒊𝒏𝒈 𝒇𝒍𝒂𝒑𝒔)
𝑚. 𝑎. 𝑐 =
2 × 𝐶 𝑅
3
(
1 + 𝜎 + 𝜎2
1 + 𝜎
)
𝑚. 𝑎. 𝑐 =
2 × 185
3
(
1 + (0.569)+ (0.569)2
1 + 0.569
)
𝒎. 𝒂. 𝒄 = 𝟏𝟒𝟖. 𝟕𝟖 𝒎𝒎 → 𝟏𝟒. 𝟖𝟕𝟖 𝒄𝒎
Calculating Lift
𝐿 =
1
2
𝜌𝑉2
𝑆𝐶𝐿
Max. CL = 1.1991 at α (10.25⁰)so,
𝐿 =
1
2
(1.255) × (5)2
× (0.29784) × (1.1991)
𝑳 = 𝟓. 𝟔𝟎𝟐 𝑵 𝒂𝒕 𝛂 (𝟏𝟎. 𝟐𝟓⁰)
This is the lift which is required in order for the flying wing to take off.

Calculating Drag
𝐷 =
1
2
𝜌𝑉2
𝑆𝐶 𝐷
Max. CD = 0.1359 at α (12.25⁰)so,
𝐷 =
1
2
(1.255) × (5)2
× (0.29784) × (0.1359)
𝑫 = 𝟎. 𝟔𝟑𝟓𝟎 𝑵 𝐚𝐭 𝛂 (𝟏𝟐. 𝟐𝟓⁰)
#Ref 10

Construction Procedures
We have chosen the blunt nose flying wing as a project for our HND final semester.
The idea of construction this project was interesting part for us then we discuss and
decided to start work on this project. First we research online for preparing “fixed
versa wing” soon we got a link and that was helpful for us then we started work
according to that idea.
Figure15: Flying wing
First of all I am going to explain the construction part of wing. To make a wing we
chose the airfoil first because that was the important part and shape of the wing
depends on it. We had needed an airfoil with a flat low chamber and upper chamber
with a curve. There were many airfoils that we tried but the result was not good
enough and we were not satisfied with that and after some research finally we
selected “AG35” that was most suitable airfoil for our wing.

The material we have chosen for whole project is ready board foam because it is
light in weight and easy to give shape. We took a large sheet of ready board foam
and cut in a required shape for a wing. We cut two pieces one for upper chamber
and the other one is for lower chamber then we started to give a shape and
dimensions to one of the piece of foam.
Figure 16: Ready board foam
To give a shape we made a sketch of a real wing on the piece by pensile then used
a sharp edge cutter to cut out the real part of wing. As soon we got the plane part of

wing again we made some lines by pensile on piece for curve and gave some holes
for electronics.
Figure 17: Lower camber of wings cut
Then we started to join both upper and lower chamber to giveairfoil shape to the
wing. For that we did some cutting especially for curve we made lines by cutter and
made holes for servos and extra hole to fix the spars. Spar is specially made to give
support to the both lower and upper chamber mainly we fixed two spar in between
the wings for more strength. The lines are made for the smooth curve at the leading
edge to decreases the air resistance. And we use glue for curve because
Reinforcing insideof the wing with hot glue will give wing long lasting strength. #Ref 1
#Ref 3 #Ref 4

Figure18: Cuts for air-foil shape and installation of servos
We left the wing for some time to cool down the hot glue that will give more strength.
After that we just put the servos and did wiring of servos. The same process we did
for the other wing and leave it till we complete the fuselage.
Figure19: Air-foil shape made with foam spar added

At this point we have done the construction almost 70% now we put all three parts
together. First we decided to join the fuselage and wings with the glow but it was not
much strong to hold the all three parts together for long there was a risk because the
glue can hold temporary but at the time of flying it can break then we selected the
epoxy as a resin to use it because it is more stronger than glue and it has a thin
layer. We started applying epoxy first between one wing and fuselage then we joint
the other wing with the fuselage as well as after some time we did taping over the
joint to make it strong. Machining it well strong and to provide strength we have fixed
spars with epoxy in between the wings and fuselage it will give a high strength to the
base of the whole project.
Figure20: Electronic installation
#Ref 1 #Ref 3 #Ref 4

Now for the middle part of the project that is fuselage we cut a piece from the sheet
of the foam and kept it more in length. Similar to wing we gave dimension and draw
ling in between the half of the piece to fold it and make deep cut from inside at same
line for better curve and fold it. We also put spars to give support to the upper
chamber.
For the fuselage we planned to fix electronics and fixe the portion for each part like
battery, servos etc. So we made a cut for motor and put it at same place, then we did
wiring of servos and battery then joined them all. There were some problem to face
because of spars that were blocking the area for wire but we cut a small piece of
spar and made a way to go through it and fixed all the connection with battery. The
construction of fuselage was completed then we fold it back and planed to close the
model finally.

The lower chamber was fully sealed already as I mention in previous slide then we
first discussed to close upper chamber & there were many options to close it like
from glue, tapping or epoxy. The epoxy was impressive strong for the joining parts
according to that we put the epoxy on edges and tighten closed all together wing and
fuselage and left for some time. It was not enough to stay for long time then also we
did taping over the joining parts then weakness was covered.
As you can see for combining the lower chamber to upper chamber we did stitching
to joint them with the best strength.
The lamination of mono-coating paper was the only option to cover the hole, cuts
and other dents that was done during the work and it gives a great smoothness that
we needed during the flight. The chance of air entering in the plane was almost over
& it was the best for airflow over the plane and giving it a smooth flight.

This is the last and important part of construction in project to fix the landing gear.
The landing gear is made up of a solid steel rod bended to get the balance. The steel
rod is welded with small metal sheet which was then attached to the bottom, same
concept for the nose landing gear.
We joined the wheels to the appropriate side. The front landing gear is placed under
the battery location of the plane and the aft landing gear was placed below the motor
ply wood. It was secured with glue and screws. #Ref 1 #Ref 3 #Ref 4

Airfoil Selection
Initial Airfoil
For our chosen UAV (fixed wing), airfoil NACA0007 is the best selection we could
make. This is a NACA 4-digit airfoil. The first 2 digits define the chamber amount and
shape. Numbers 00 means that airfoil has zero camber and therefore it is fully
symmetrical. The last two digits define the thickness of the airfoil as per the
percentage of the length. NACA 0007 is a 7% thickness airfoil so an airfoil with 10”
chord will be 0.700” thick at the thickest point of its profile.
We used this airfoil because the kind of lift needed can only be generated by this
airfoil. This is a symmetrical airfoil with a lot of advantages for instance it is very
good in terms of aerobatics. It is very useful for pattern flying. It gives a better lift to
drag ratio and more lift at given speed as compare to a semi symmetrical airfoil. The
movement of the centre of pressure of symmetrical airfoil is less than with cambered
airfoils. The kind of lift we expect from our UAV can only be achieved from airfoil
NACA 0007.
 NACA 0007 has a maximum thickness of 7% at 29.7% of the chord.
 Maximum camber is 0% of the chord
 Leading edge radius is 0.6024%.
 Trailing edge thickness is 0.1470

Improved airfoil for better lift
For our chosen UAV (fixed wing), mark drela AG-11 air-foil is the best selection we
could make. This is intended for low Reynolds number and laminar flow. Mostly used
for small hand launched aircraft or may use for gliders. It is about 5.8 % thick and
has a relatively flat bottom which makes it easier to fabricate. Aircraft using this kind
of air foil is better to carry enough weight and have more stability and predictability.
This air foil is known as conventional air foil with low chamber and having the least
drag while achieving the high speed.
This is a conventional airfoil with a lot of advantages for instance it is very good in
terms of aerobatics .We used this because the kind of lift needed can only be
generated by this .It is very useful for pattern flying. It gives a better lift to drag ratio
and more lift at given speed as compare to symmetrical airfoil. The movement of the
centre of pressure of conventional airfoil is less than the symmetrical air foils. The
kind of lift we expect from our UAV can only be achieved from airfoil AG-11
 AG-11 has a maximum thickness of 5.81% at 25.4% of the chord.
 Maximum camber is 2.29% at 29.1% of the chord
 Leading edge radius is 0.6035%.
 Trailing edge thickness is 0.2321%

Figure25: AG11 shape
This airfoil was rejected by our instructor Mr. Islam and suggested to change as this
AG11 has inappropriate thickness according to our flying wing RC plane design. The
thickness was too less as the plan was to put spar for the airfoil shape and it seemed
inappropriate. So we changed the airfoil to a better thickness and flat bottom.

FINAL AIRFOIL SELECTION
For our chosen UAV (fixed wing), airfoil AG35 is the best selection we could make.
This is a AG35 airfoil. The last two digits define the chamber amount and shape.
Numbers 35 means that airfoil has almost flat lower camber and therefore it is fully
symmetrical. The last two digits define the thickness of the airfoil as per the
percentage of the length. AG35 is 8.7% thickness airfoil so an airfoil with 27.9” chord
will be 8.7” thick at the thickest point of its profile. Planes with this airfoil can carry
more weight and are more stable and predictable.
We used this airfoil because the kind of lift needed can only be generated by this
airfoil. This is a symmetrical airfoil with a lot of advantages for instance it is very
good in terms of aerobatics. It is very useful for pattern flying. It gives a better lift to
drag ratio and more lift at given speed as compare to a semi symmetrical airfoil. The
movement of the centre of pressure of symmetrical airfoil is less than with cambered
airfoils. The kind of lift we expect from our UAV can only be achieved from airfoil
AG35.
 Drela AG35 has a maximum thickness of 8.7% at 27.9% of the chord.
 Maximum camber is 2.3% of the chord at 37% of cord
Figure26: AG35 shape and thickness

AG-35 Airfoil Graphs:
Figure27: Graphs of CL/CD and CL/alpha
Figure28: Graphs of Cm/alpha and CD/alpha
#Ref 4

(AG-35) Polar data table
Alpha Cl Cd Cdp Cm Top Xtr BtmXtr
-11.0000 -0.3782 0.1037 0.0991 -0.0110 1.0000 0.0941
-10.7500 -0.3839 0.1004 0.0958 -0.0132 1.0000 0.0977
-10.5000 -0.4920 0.1063 0.1014 -0.0040 1.0000 0.0894
-10.2500 -0.4848 0.1029 0.0980 -0.0045 1.0000 0.0927
-10.0000 -0.4846 0.0995 0.0947 -0.0073 1.0000 0.0967
-9.7500 -0.5013 0.0965 0.0918 -0.0165 1.0000 0.0992
-9.5000 -0.4991 0.0912 0.0867 -0.0193 1.0000 0.1008
-9.2500 -0.4790 0.0882 0.0835 -0.0129 1.0000 0.1047
-9.0000 -0.4756 0.0846 0.0800 -0.0157 1.0000 0.1093
-8.7500 -0.4836 0.0785 0.0739 -0.0314 1.0000 0.1145
-8.5000 -0.4663 0.0760 0.0715 -0.0231 1.0000 0.1186
-8.2500 -0.4670 0.0709 0.0662 -0.0362 1.0000 0.1285
-8.0000 -0.4502 0.0683 0.0637 -0.0282 1.0000 0.1334
-7.7500 -0.4436 0.0636 0.0590 -0.0338 1.0000 0.1443
-7.5000 -0.4311 0.0609 0.0562 -0.0347 1.0000 0.1557
-7.2500 -0.4206 0.0571 0.0525 -0.0334 1.0000 0.1610
-7.0000 -0.4099 0.0538 0.0491 -0.0344 1.0000 0.1740
-6.7500 -0.3981 0.0509 0.0461 -0.0345 1.0000 0.1881
-6.5000 -0.3673 0.0365 0.0302 -0.0412 1.0000 0.0898
-6.2500 -0.3435 0.0317 0.0241 -0.0400 1.0000 0.0724
-6.0000 -0.3244 0.0283 0.0204 -0.0392 1.0000 0.0736
-5.7500 -0.3028 0.0260 0.0177 -0.0382 1.0000 0.0741
-5.5000 -0.2797 0.0239 0.0153 -0.0371 1.0000 0.0744
-5.2500 -0.2564 0.0222 0.0134 -0.0362 1.0000 0.0765
-5.0000 -0.2330 0.0211 0.0121 -0.0353 1.0000 0.0826
-4.7500 -0.2081 0.0197 0.0106 -0.0345 1.0000 0.0878
-4.5000 -0.1837 0.0186 0.0095 -0.0339 1.0000 0.0961
-4.2500 -0.1590 0.0177 0.0086 -0.0334 1.0000 0.1105
-4.0000 -0.1336 0.0167 0.0078 -0.0331 1.0000 0.1335
-3.7500 -0.1062 0.0154 0.0070 -0.0333 1.0000 0.2121
-3.5000 -0.0803 0.0133 0.0068 -0.0331 1.0000 0.6051
-3.2500 -0.0568 0.0125 0.0068 -0.0307 1.0000 1.0000
-3.0000 -0.0351 0.0128 0.0068 -0.0303 1.0000 1.0000
-2.7500 -0.0025 0.0131 0.0068 -0.0320 0.9963 1.0000
-2.5000 0.0538 0.0133 0.0068 -0.0381 0.9844 1.0000
-2.2500 0.1092 0.0135 0.0067 -0.0439 0.9711 1.0000
-2.0000 0.1644 0.0135 0.0066 -0.0495 0.9571 1.0000
-1.7500 0.2189 0.0135 0.0065 -0.0548 0.9426 1.0000
-1.5000 0.2687 0.0134 0.0063 -0.0588 0.9269 1.0000
-1.2500 0.3085 0.0133 0.0061 -0.0607 0.9067 1.0000
-1.0000 0.3442 0.0133 0.0060 -0.0615 0.8863 1.0000
-0.7500 0.3751 0.0132 0.0058 -0.0613 0.8658 1.0000
-0.5000 0.4012 0.0132 0.0058 -0.0602 0.8429 1.0000
-0.2500 0.4269 0.0132 0.0057 -0.0590 0.8223 1.0000
0.0000 0.4515 0.0133 0.0057 -0.0577 0.8007 1.0000
0.2500 0.4765 0.0134 0.0057 -0.0564 0.7814 1.0000
0.5000 0.5010 0.0135 0.0057 -0.0553 0.7601 1.0000
0.7500 0.5260 0.0137 0.0058 -0.0542 0.7403 1.0000
1.0000 0.5512 0.0138 0.0059 -0.0532 0.7218 1.0000
1.2500 0.5763 0.0140 0.0061 -0.0524 0.7012 1.0000
1.5000 0.6017 0.0142 0.0062 -0.0516 0.6818 1.0000
1.7500 0.6273 0.0143 0.0063 -0.0507 0.6631 1.0000
2.0000 0.6526 0.0145 0.0064 -0.0500 0.6424 1.0000
2.2500 0.6782 0.0147 0.0066 -0.0491 0.6234 1.0000

2.5000 0.7036 0.0150 0.0068 -0.0484 0.6029 1.0000
2.7500 0.7288 0.0154 0.0072 -0.0477 0.5815 1.0000
3.0000 0.7540 0.0159 0.0076 -0.0470 0.5599 1.0000
3.2500 0.7788 0.0163 0.0080 -0.0463 0.5368 1.0000
3.5000 0.8034 0.0167 0.0083 -0.0456 0.5129 1.0000
3.7500 0.8280 0.0170 0.0086 -0.0448 0.4889 1.0000
4.0000 0.8519 0.0173 0.0090 -0.0439 0.4615 1.0000
4.2500 0.8758 0.0175 0.0092 -0.0431 0.4332 1.0000
4.5000 0.8992 0.0178 0.0095 -0.0422 0.4038 1.0000
4.7500 0.9222 0.0183 0.0098 -0.0414 0.3736 1.0000
5.0000 0.9447 0.0188 0.0104 -0.0405 0.3420 1.0000
5.2500 0.9668 0.0195 0.0110 -0.0397 0.3112 1.0000
5.5000 0.9884 0.0203 0.0117 -0.0388 0.2816 1.0000
5.7500 1.0093 0.0211 0.0125 -0.0380 0.2527 1.0000
6.0000 1.0297 0.0221 0.0134 -0.0371 0.2248 1.0000
6.2500 1.0492 0.0231 0.0144 -0.0361 0.1979 1.0000
6.5000 1.0679 0.0243 0.0155 -0.0351 0.1721 1.0000
6.7500 1.0854 0.0255 0.0166 -0.0340 0.1474 1.0000
7.0000 1.1021 0.0268 0.0179 -0.0327 0.1235 1.0000
7.2500 1.1179 0.0284 0.0196 -0.0314 0.1034 1.0000
7.5000 1.1336 0.0302 0.0214 -0.0300 0.0872 1.0000
7.7500 1.1494 0.0322 0.0234 -0.0287 0.0750 1.0000
8.0000 1.1668 0.0347 0.0259 -0.0276 0.0669 1.0000
8.2500 1.1825 0.0365 0.0279 -0.0263 0.0600 1.0000
8.5000 1.1987 0.0396 0.0312 -0.0252 0.0556 1.0000
8.7500 1.2121 0.0425 0.0345 -0.0236 0.0527 1.0000
9.0000 1.2234 0.0452 0.0374 -0.0222 0.0499 1.0000
9.2500 1.2350 0.0487 0.0410 -0.0214 0.0471 1.0000
9.5000 1.2332 0.0523 0.0450 -0.0191 0.0459 1.0000
9.7500 1.2271 0.0557 0.0489 -0.0166 0.0453 1.0000
10.0000 1.2154 0.0593 0.0529 -0.0140 0.0451 1.0000
10.2500 1.1991 0.0631 0.0570 -0.0118 0.0451 1.0000
10.5000 1.1805 0.0673 0.0614 -0.0107 0.0451 1.0000
10.7500 1.1603 0.0721 0.0664 -0.0109 0.0453 1.0000
11.0000 1.1389 0.0775 0.0721 -0.0123 0.0455 1.0000
11.2500 1.1167 0.0836 0.0784 -0.0148 0.0458 1.0000
11.5000 1.0943 0.0906 0.0855 -0.0184 0.0462 1.0000
11.7500 1.0724 0.0982 0.0933 -0.0225 0.0465 1.0000
12.0000 0.9687 0.1281 0.1234 -0.0444 0.0567 1.0000
12.2500 0.9591 0.1359 0.1312 -0.0473 0.0574 1.0000
#Ref 4

Comparing Airfoils (AG35-il, USA35b-il, E178-il, GOE566-il)
Plot Airfoil Reynolds # Ncrit Max Cl/Cd Description
ag35-il 100,000 9 50.5 at α=4.75° Mach=0 Ncrit=9
usa35b-il 100,000 9 53.3 at α=6.75° Mach=0 Ncrit=9
e178-il 100,000 9 56.3 at α=7° Mach=0 Ncrit=9
goe566-il 100,000 9 52.4 at α=4.5° Mach=0 Ncrit=9
Figure29: Comparison graphs of Ag35, USA35b-il, E178-il, GOE566-il
#Ref 4

Problems & Trouble shooting
Problems occurred during construction of project
1) Problem 1
During the construction of the model, we came across several challenges; one of the
main problems we faced was the shaping of airfoil in wings and the centre body.
Since our model was a whole flying wing that includes a centre body, so shaping the
wings and the centre body as according to the our selected airfoil shape, which was
AG-35 was the most critical part of our construction of the model.
To start off with the cutting of the wings, we followed a technique of cutting the two
chambers upper and lower separately, and then join the two chambers by applying
hot glue on it, for a stiff joint. But later we realized that joining the two chambers
separately was not giving the proper airfoil shape and in turn it was very hard to even
maintain the shape. As the cutting was already done we tried to at least give the
proper required airfoil shape, which was necessary to provide us with laminar airflow
over the wing.
So we went onto discuss this issue with our project instructor, so the instructor asked
us to find a solution in order improve the frontal curvature so as to provide a smooth
laminar airflow, since our front area was not having proper airfoil curve and was a bit
flat instead leading towards the turbulent airflow.

Troubleshooting
After discussing with the instructor we actually realized that this will not work and
later there will be issues in the design of the model. So we focused on how to deal
with the problem after analyzing several parameters which were important to be
considered, we came up with an idea of re-constructing the wings. As it was a good
idea rather than improving the wing which was already designed, because the
material used was foam and it was not that difficult to do the whole process again.
So we started with the re-construction process of the wings, and our idea now was to
construct the wing with one single piece of foam rather two different pieces, so we
carried on further with the construction of wings on a single piece and give about
75% cutting to give a proper curvature on the upper chamber and this was the best
possible method as according to this the airfoil shape was being maintained and in
turn it was strong enough as compared to the previous design.
2) Problem 2
After reconstructing the wings and centre body we joined the wings with the centre
body according to the airfoil shape selected which was AG-35. When the model was
constructed and joined we realized that it wasn’t stiff enough to maintain its design
during flying under high pressure due to the airflow. As the spars included were
made up of foam itself which was decided by our group earlier. After discussing the
issue with instructor we came to know that our concern regarding stiffness and
strength was genuine and the wings were not balanced leading the model to flutter in
strong wind due to the weak structure of the design.

Troubleshoot
To overcome this problem, we decided to add spars or ribs made of stronger and
durable material in order to give a better stability and strength in the model. So we
decided to choose a materialwhich is stronger yet lighter in weight, so the overall
estimated weight of our design is not much affected. Keeping this strength-to-weight
ratio factor in mind, we decided to select balsa wood to use for making spars, since
the balsa wood possess a very reliable strength to weight ratio and is widely used in
the building of such engineering projects. We added two spars on each wing to
provide the utmost strength and two in between the centre body connecting it with
wings to hold the model together.

Troubleshooting for Transmitter and Receiver
The mode of communication in our flying wing, or any RC plane is through radio
signals which are carried along with the help of hand held transmitter, sometimes
there is a problem that the model does not respond properly to the radio signals
transmitted.
So in this case the following steps were taken into consideration that might helps in
troubleshooting the transmitter/receiver problems:
i. Check ON/OFF switches: Make sure that the switches on the model and as
well as transmitter are turned ON.
ii. Check Frequency: It is important that the frequency of the transmitter and
the receiver match.
iii. Check Battery: Make sure the battery is fully charged and thus
properlyinstalled with all connections properly connected.
iv. Check Servos: If the servos do not respond to the commands routed by the
transmitter there might be some problems with the servos itself, so in this
case you must try unplugging your servos from the receiver and reconnect
them, if the problem is still not been resolved than double check again and try
to repair or hence replace them.

Safety precautions
The safety precautions are very important when constructing an RC plane and they
must be kept in mind at all the times for better environment damages and human
errors. The precautions are as follows:
 A proper site for flying the airplane must be checked.
 Prevent damages that can be caused during flight to the public property or
moving vehicles which could result in expenses.
 Carryout pre-flight checks for the flaps, ailerons, motor movement and ground
test for risk assessment.
 Be aware of radio gear battery levels so that it does not go out of charge
during flight.
 Handling of tools during construction is important for a safe environment so
the use of cutter must be handled carefully.
 Use of drill machine must be precise and safe, as it can cause serious
damage if used carelessly.
 The hot glue gun gives out glue with very high temperature so make sure the
front part and glue doesn’t touch body parts.
 Using of laminating iron must be safe and temperature must be adjusted to a
specific given.
 While tightening the screws, make sure to not to slip the handle other wise it
can cause material damages and pain on fingers.
 Wear gloves and eye protection while making holes in material by the drill
machine.
 Keeping the iron and hot glue gun away from the body so that it does not the
clothes or body.
 Making a circuit diagram first for electronics so that wires don’t short circuit
when connected.
#Ref 13

CONCLUSION
In this project report we discussed a flying wing design and presented critical
information which was necessary when considering the process of construction while
building the proposed model. There are several parameters which are confronted
when starting with the process of construction. Although our project failed to
accomplish its desired objectives but it provided us plenty of knowledge and
understanding regarding the project evaluation techniques. We learned some facts
about the project while implementing the construction which could not have been
possible through only understanding the theoretical research. We inherited a-lot of
knowledge about UAV’s by working on this model. Our proposed model did not only
required the technical knowledge but it also allowed us to implement the theoretical
knowledge we learned in previous semesters. The major subject which help us a lot
in constructing this project were Aerodynamics, Propulsion, analytical methods etc.
We faced a lot of problems in construction of wings as there were several features
which needed utmost consideration which we didn’t focused on while moving along
with the construction process and then we had to change the design as per the
guidance of Mr. Islam Zaki. We learned the required techniques related to designing
the model with the aid of 2D and 3D designing software’s such as AutoCAD. We did
some electrical work on our project which increased our knowledge about the
avionics of RC planes and we finally got chance to apply the knowledge which we
learned. There were some problems faced which were recovered as we proceeded
with the construction. This project gave us an exposure of working in an environment
where we have to work as a team. Due to the individual efforts of all the members
working as a team for the desired objective it helped us in achieving aim of the
project in the best possible way. The university resources provided us with
necessary equipment and knowledge which was crucial for the construction. It was a
great learning experience for which I would like to thank our instructor for giving us
this opportunity of constructing the aircraft which helped us a lot in gaining the
knowledge related to aviation industry. I hope you enjoyed reading this report and
came across the required information you were looking for which is crucial for an
aeronautical engineer in understanding the project evaluation techniques.

APPENDIX

Proposals
Parametric Study 1
FIXED WING FPV: SkyVU-10
Purpose and Aim:
Built from indestructible moulded EPP foam board, it is a medium size yet low-cost
wing capable of carrying a full-feature HD camera such as the Go-Pro while keeping
the all-up-weight in the 600g-1200g range. Having a smooth, low drag design it
performs smoothly and efficiently in sky. It utilizes accessories that are of exceptional
quality and provides the freedom to use the plane with any FPV equipment,
powertrain and battery system, while reducing the building time to a minimum when
using it with TBS- or TBS-compatible equipment.
SkyVU-10, a fixed wing FPV(First-person view) which is generally a medium-sized
yet low cost UAV airframe having sufficient payload space for the video equipment
and large wings capable of supporting the extra weight during flight. This concept of
fixed wing aircraft utilizes a pusher propeller configuration, allowing for a "prop free"
image on either the live video feed or the High Definition recording using camera
planted on the airframe.
Flying as an UAV(Unmanned Ariel Vehicle), FPV SkyVU-10 can be deployed at the
front lines for agriculture monitoring and to Survey damaged or assess conditions in
inaccessible, hazardous or contaminated areas and many more multipurpose
monitoring, such as :
 Animal Monitoring and Tracking in wild areas
 Provide geospatial references and navigation
 Traffic Monitoring
 Military Use for Border Patrol and to Assist Search and Rescue Operations
 Police Use to monitor the movement of people & vehicles in case of jail
break.
 Agricultural Monitoring and Pipeline Monitoring
 Localized surveillance
 Videography/Photography over crowd and rush during events.

Design:
*Note: Not to scale
Overview of the fixed wing.
Figure23: Flying wing concept

Specifications& Materials:
 Wingspan: 1200mm (48’’ inches)
 Wing chord- 6’’ inches
 Fuselage length- 10’’ inches
 Fuselage width- 8’’ inches
 Total Weight estimation: 1000-1200g (including Camera/Battery/wires)
 Motor- 1200-1400kV
 Speed Controller: 12-18A ESC
 Propulsion Power System: 8in-12in Propeller
 Receiver: 3 Channels or more
Required Tools:
 Utility Knife (Blade)
 Storage tape
 Glue
 Hot Glue Gin
Advantages of Fixed-Wing FPV over a Multi-rotor
 Longer flight times.
 More space to set up the FPV gear (ex: the wings).
 Larger wing area allows to support more weight during flight.
 Cheaper in cost as compare to multi-rotors.
 Can glide if battery fails.
Disadvantages:
 Can't hover on grounds.
 Can't carry bigger cameras.
 Requires more space to fly.
To conclude about fixed-wing FPV plane (UAV) over multi-rotor, I think they are a
better platform for people who want to go on longer ranges for longer duration, and
are also interested in aerial photography/videography.

Parametric study 2
MINI GUINEA RC
Mini GUENIA is a small twin propeller UAV. This mini Guinea is capable of wide
variety of manoeuvres such as flat spins, pin wheels and even harriers. Due to twin
propeller engine property this plane has the ability to achieve height up-to 150 feet’s
which is very good considering the size of aircraft. But if we build a bigger model of
the same aircraft it could certainly achieve much more height and could be very
useful for cargo transportation in remote areas during flood or other natural
disastrous strikes. Our design could fly around 25 minutes of estimated time which is
enough to perform any small transportation stunt to convince our instructor.
These aims and objective include:
1. Camera: A camera is to be installed for traffic surveillance, park monitoring,
animal monitoring in zoos etc.
2. During war conditions landing operation is not possible hence medicines and
other food resources could be delivered to the soldiers and other civilians.
3. During flood due to no landing option food and medications could be delivered
to people.
4. Watering/pesticides the plants by attaching the small tank in the belly.
Figure24: Mini guinea concept
Our chosen UAV has under-cambered wing tips which give this aircraft a very wide
speed envelope and it allows anything from slow high flight to fast sport flying. Our
basic purpose of choosing this aircraft is for transportation of goods. This can be
achieved adding up one more servo motor to the air craft belly connecting it to the
receiver, and operate it during the flight operation by opening the belly gate of the
aircraft and releasing the goods attached to the belly to the respected destination

without landing the plane. Our chosen UAV could be used for localized surveillance
by just adding up a camera with the GPS for monitoring and tracking.
ADVANTAGES:
 An attached camera can be useful in monitoring and surveillance for security
and other recording purposes.
 Its advantages are that landing is not required and we could just drop off the
things.
 During war conditions landing operation is not possible hence medicines and
other food resources could be delivered to the soldiers and other civilians.
 During flood due to no landing option food and medications could be delivered
to people.
All these things could be done by decreasing the altitude of the aircraft which is quiet
possible for them.
Specifications and Requirements:
 Weight without battery- 250-300g
 Total weight estimation (camera, battery, speed controller) – 1.2-1.4Kg
 Motor– 1400-1800KV
 Wingspan- 35’’ inches
 Wing chord- 6.4’’ inches
 Battery - 460mah 3S 25~40C Li-po Pack
 Prop (Option 1) - Direct Drive HQ Prop - 5x3 Black
#Ref 12

Parametric study 3
Pool noodle 3D plane
Aim and objective
First of all, our main purpose for this particular RC plane is that we fit a bird (toy) on
top of it which will be chased by hawk/eagle in competitions in UAE. This is helpful
as this plane will have the ability to pitch, roll, yaw and perform other manoeuvres
with the help of rudder, elevator and ailerons. This is kind of hobby which is preferred
in UAE and can be used in ‘bird chasing competition’.
Figure25: Pool noodle concept
Advantages and disadvantages
The biggest advantage is that this particular pool noodle 3D plane is very in-
expensive and can be built from lightweight materials such as the carbon fibre rod
and surfaces from thicker depron sheet, whereas on the other hand, this plane might
not able to reach high altitudes (250+ft) due to the requirement of heavy and bigger
battery. This plane may not be super strong and might not be able to withstand crash
landing such as structural damage to the airplane.

Specifications
1. Length- 28’’
2. Fuselage diameter- 2.4’’
3. Fuselage weight- 8 pounds
4. Wing span- 34’’
5. Wing chord- 9’’
6. Total weight estimation- 1000g
7. Motor- 1750KV
#Ref 9
Design Concept

Proposal Report
After doing much of research and comparing our all 3 proposals, we would prefer to
go with Fixed wing FPV SKYVU-10. To conclude about fixed-wing FPV planes(UAV)
over multi-rotor, I think they are a better platform for people who want to go on longer
ranges for longer duration, and are also interested in aerial photography/video.
The 2nd reason for choosing fixed-wing FPV is that it has got great stability control
plus manoeuvrability and most importantly it can give better view for FPV purposes,
Requires lesser parts to perform the same tasks as FT Mini Guinea, and is low
budget as compared to Mini Guinea.
They are easy to build, less parasite drag as compare to Mini Guinea. Fixed wing
SkyVU-10 haslarge wing span which is capable of supporting the extra weight during
flight.This UAV plane will be constructed fairly and will lie in our budget.
The project on building fixed wing SkyVU-10 will be a great experience and we
expect to develop new ideas after the modification to the plane. This will also give us
great opportunity to do practical work and help us in future.
ADVANTAGES
 This model of RC plane doesn't to design and make fuse large.
 As the wing design is delta shaped so it is drag less sensitive to Mach
number.
 This aircraft has good maneuverability.
DISADVANTAGES
 Low wing loading.
 Complicated Design.
 Tailless deltas have high landing speeds and bad field performance.

Evidence of project
Picture26: Construction of the lower camber wing by habib and qayum.
Picture27: Shows faisal doing construction
of the holes for securing of the spars on
lower camber.
Picture28: Shows the ahmed and
shoaib putting hot glue gun in the
inner cuts for better strength of airfoil
shape.

Picture29: Shows the habib and ahmed sticking the balsa wood spar into the
wing for better strength of the airfoil shaped wing.
Picture30: Shows the group members working on the electronic part while the
wings and fuselage is not closed for airfoil shape.

Tools for construction
Figure31: Cutter
This cutter was used in almost every part of the construction. The first cutting of the
foam with wings shape, cutting of the inner cuts for airfoil shape, cutting of the balsa
wood spar, cutting of the winglets.
Figure32: Scale
The scale was used to measure all the dimensions we made such as fuselage
length, width, airfoil thickness etc.
Figure33: Hot glue gun and fevicol glue
Fevicol and most importantly glue gun was use for joining of the wings tip, fuselage
tip, spar joints, winglet, camera attachment, screws etc.

Figure34: Duct Tape
It was used for joining winglets, joints of wings and fuselage lower camber.
Figure35: Screwdriver and screws
Figure36: Drill machine and drills
Drill machine was used to for drilling on the firewall for motor, attachment of sheet on
fuselage and camera.

Figure37: Laminating sheet iron
Laminating sheet iron was used for sticking the sheet on the whole outer surface of
the plane. The temperature is adjustable on this iron.

Material/component Used
Figure38: Ready board tree foam (5mm thickness)
Ready board foam is used to construct this RC plane. There were other options as
well but due to unavailability of EPP foam in UAE we selected ready board.
Figure39: Gens Li-po battery 11.1v 2700mah 25c 3SIP
The battery was bought with the reference of a similar aircraft of similar wingspan
and other parameters. This 2700 could provide our plane a flight time of 6-8 minutes.
Figure40: Suppo SP-90 9gMicro servo
Two 9g servos were used for controlling ailerons. They are light weight and perform
good job.

Figure41: SF E-Prop 12 by 6
The propeller of 12*6 was selected as we planned to have enough gap between the
ground and plane & between the two flaps.
Figure42: Turnigy 2730 Brushless Motor 1000 vKv
A 1000vkV brushless motor was selected by performing a calculation on power
required. It is 3C motor which is suited for great range of ESC.
Figure43: Turnigy Plush 30amp Speed Controller.
A 30Amp ESC was used for 1000vkv motor which is appropriate for the required
amount of power.

Figure44:Go Pro hero 4 camera
A light weight rechargeable camera recorder was used for recording a HD video with
a simple step and simple memory card. This camera is compact in size and
toughness.
Figure45: 5 channel transmitter (Remote)
A 5 channel transmitter was appropriate is selected as there were only 3 channel
required for the flight. The 3 channel required are for 2 servos and 1 ESC.
Figure46: Landing gear (2 sets, front & aft)
The landing gear was constructed with 2 steel rods bended to a proper angle and
height. The plan was to attach the nose landing gear below the battery and aft gear
below the motor firewall which might give a better stability. #Ref 1 #Ref 3

WEIGHT ESTIMATION OF EACH COMPONENT OF RC PLANE
SI.N0 Component Image Weight
1 Li-po battery 7.4v 2800mah 30c
max 50C
170
2 Turnigy 2730 Brushless Motor 1000
Kv
75
3 Turnigy Plush 30amp Speed
Controller.
22g
4 SF E-Prop 8*6 60g
5 Suppo SP-90 9gMicro servo
(2pcs*9g=18g)
18g
6 Foam 300g
7 Receiver 35g
8 GO-pro camera 150g
9 Landing gear 100g
TOTAL WEIGHT
= 930g

ACTUAL WEIGHT OF EACH COMPONENT
SI.N0 Component Image Weight
1 Li-po battery 7.4v 2700mah 30c 196g
2 Turnigy 2730 Brushless Motor 1000
Kv
120g
3 Turnigy Plush 30amp Speed
Controller
25g
4 SF E-Prop 8*6 60g
5 Suppo SP-90 9gMicro servo
(2pcs*9g=18g)
18g
6 Foam 340g
7 Receiver 10g
8 Recording camera 114g
9 Landing gear 200g
10 TOTAL WEIGHT 1090g

Testing
Testing before Flight Test
Once our model was ready with the construction, we planned to test it on ground
before the flight test. While testing the model we came across certain issues which
needed serious consideration.
The major consequence we faced was that the flaps weren’t moving accurately, the
angle provided by servos wasn’t sufficient enough to start with the flight. As they
needed to be moved together as well as simultaneously in order to provide the turn
when required. But we realized that the servos weren’t working properly. After series
of efforts we came to know that there was some problem with the transmitter control
due to which servos weren’t providing 100% work as required. And finally the issue
with the servos was resolved.
Secondly, as we decided to test the flying wing on the ground there we confronted
another problem which was a foremost issue in attaching the landing gears. The
front landing gear was not attached at the right angle to the rod due to which when it
was moving on the ground it was not capable of going a straight line. It was going
towards right direction, as the landing gear was fixed with the wing through welding
so this was hindering us to apply any force to relocate the hinge through which the
landing gear was attached. Somehow we tried our level best to move it and attach
the wheel again, we applied this technique several times and did the testing again
but it didn’t provide us with some distinctive difference. Unfortunately due to the
shortage of time as it was the day when flight test was going to be done we weren’t
able to fix this issue. Another reason which was causing it to change its direction was
the terrain the location where flight test was supposed to be done was pretty rough
and our model demanded a smooth surface. It managed to take off but didn’t make it
way further.
All these were the issues that we came across while constructing and testing the
flying wing model. After all the techniques and procedures we applied for the
troubleshooting. It gave us a plenty of knowledge despite the fact that during the
ground testing our model was coming across some consequences which required
utmost attention.

Flight Test
As the problem of plane not going in a straight line was improved with some
adjusting of the nose landing gear rod and angle of tire, it was time to do the flight
test. We were stuck with the uneven tiled surface which was not suitable for the
plane but had no other choice. The Battery was connected and controls surfaces
were checked before giving it a throttle. The idea of flying was to increase the throttle
gently at first and hard after 10 meters and flaps slowly increasing once it reaches
takeoff speed. Using this idea, the throttle was given and plane got a bit of turn. The
takeoff speed was achieved where elevators were fully up, it took off in a right
direction and flip crashed. Nothing was damaged and gave it another try. Same
starting procedure was given as before and this time it did not move off the ground.
For the third attempt, the deflection of elevators was checked and adjustments were
done. It gained very high speed and as a result the firewall (motor holder) broke off
of the plane along with the propeller and screws. The firewall was damaged as
shown below.
Rectifications/solutions
1. The trouble shooting for this crash and damage was to add a smooth surface
or another ply wood to close the firewall triangle so that the main wall which
was facing the air shouldn’t result in breakage which was due to the high
speed air pressure exerted.
2. The solution for generating the lift is by using bigger servos and stronger
linkage rods for elevators which can stand strongly when made to move up for
takeoff. The current servos and linkage rods wasn’t strong enough to
withstand the air pressure. If the elevators were strong like a wall facing the
air, it could have resulted in nose up for takeoff.
3. Third solution is the centre of gravity which was a bit behind the calculated
Centre of gravity. The first attempted crash was due to the less weight in front
then the aft which resulted in vertical takeoff.
4. Another mistake which was done is that we did not arrange a professional
person for flying this plane so the plane could have flied if the professional
was hired.
#Ref 14

Picture47: Damages after crash
As it can be seen that the front air facing firewall broke off due to very high speed
which resulted in motor hanging and propeller removal. This firewall was joined by
the tin sheet with screws to cover and secure the joining points.

REFERENCES
#Ref 1-http://flitetest.com/articles/let-s-fly-blunt-nose-versa
#Ref 2-http://fwcg.3dzone.dk/
#Ref 3-http://www.rcpowers.com/community/threads/ft-blunt-nose-versa-
wing.17141/
#Ref 4-http://airfoiltools.com/
#Ref 5-http://red20rc.org/fpv-wing-v3-blunt-nose-versa-wing/
#Ref 6-https://www.youtube.com/watch?v=MAEnYX4UWB8
#Ref 7-https://www.youtube.com/watch?v=cHNqPk___wE
#Ref 8-https://www.youtube.com/watch?v=qDZLqpoTq6w
#Ref 9-http://www.rcsparks.com/how-to-build-your-own-pool-noodle-rc-
Ref 10-3d-trainer-airplane/
#Ref 10- Aerodynamics principles and aircraft design
#Ref 11- https://torrentz.eu/search?q=autocad+2016
#Ref 12- http://flitetest.com/articles/ft-mini-guinea-build
#Ref 13- http://www.rc-airplane-world.com/rc-flying-dos-and-donts.html
#Ref 14-http://forum.flitetest.com/showthread.php?4365-When-to-use-
flaps
#Ref 15- http://www.profili2.com/

Figures
Figure13:http://www.yoctopuce.com/pubarchive/2012-
05/plane_schematics_en_1.png
Figure14:http://fwcg.3dzone.dk/
Figure25:http://www.profili2.com/
Figure26:http://www.profili2.com/
Figure27:http://airfoiltools.com/
Figure29:http://airfoiltools.com/
Figure24:http://assets.flitetest.com/article_images/medium/miniguineabu
ild-1-png_1417798479.jpg
Figure25:http://i.ytimg.com/vi/UlNHtNGFBDA/hqdefault.jpg

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