1.
1
Aero-chopper
(VTOL)
Supervisor: Mr. Nasser Chakra
by,
Shashank Dathatreya

2.
2
Table of Content
INTRODUCTION
...............................................................................................................................
4
UAV
Types
...................................................................................................................................
6
Understanding
the
Project
..............................................................................................................
8
AIM
..............................................................................................................................................
8
ABSTRACT
....................................................................................................................................
8
SCOPE
..........................................................................................................................................
8
Parametric
Study
...........................................................................................................................
10
Specifications
and
details
..........................................................................................................
12
Specifications
and
details
..........................................................................................................
14
GANTT
CHART
................................................................................................................................
17
DESIGN
CONCEPT
..........................................................................................................................
19
COST
ANALYSIS
..............................................................................................................................
21
MAN
POWER
.................................................................................................................................
23
Cost
analysis
..................................................................................................................................
24
Cost
of
materials
and
electricals
...............................................................................................
26
Materials
.......................................................................................................................................
27
Tools
..........................................................................................................................................
30
ELECTRICALS
..............................................................................................................................
32
Overview
...................................................................................................................................
33
Overview
...................................................................................................................................
35
Airfoil
Selection
.............................................................................................................................
42
AIRCRAFT
DESIGN
..........................................................................................................................
47
Structure
designing
:(PROFILI)
.......................................................................................................
49
3D
Drawing
....................................................................................................................................
54

3.
3
CONSTRUCTION
(ASSEMBLY)
........................................................................................................
58
GRAPHS
.........................................................................................................................................
74
Area
Calculation
............................................................................................................................
78
PERFORMANCE
ANALYSIS
.............................................................................................................
97
CENTRE
OF
GRAVITY
....................................................................................................................
128
PERFORMANCE
ANALYSIS
...........................................................................................................
132
Troubleshooting
..........................................................................................................................
135
Safety
and
Risk
Assessment
........................................................................................................
138
CONCLUSION
...............................................................................................................................
139

4.
4
Acknowledgement
Of the many people who have been enormously helpful in the preparation of this
project, we are especially thankful to, Mr. Nasser Chakra for his help and
support in guiding us to through to its successful completion.
We would also like to extend our since gratitude to Emirates Aviation College for
the use of their resources, such as online databases and library, without which
the completion of this project would have been extremely difficult.
A very special recognition needs to be given to Ms. Kavita, our librarian, for her
extensive help and support during research and in dealing with online resources.
In addition, a special thanks to our friends Cibin, Suraj and Yogesh for their help,
consideration and guidance.
Last but not least, we would like to say a special thank you to our parents and
family members for their moral and financial support this semester.

5.
5
INTRODUCTION1
Figure
1
UAV
is
an
acronym
for
Unmanned
Aerial
Vehicle,
which
is
an
aircraft
with
no
pilot
on
board.
UAVs
can
be
remote
controlled
aircraft,
for
example,
flown
by
a
pilot
at
a
ground
control
station,
or
can
fly
autonomously
based
on
pre-­‐programmed
flight
plans
or
more
complex
dynamic
automation
systems.
UAVs
are
currently
used
for
a
number
of
missions,
including
reconnaissance
and
attack
roles.
To
distinguish
UAVs
from
missiles,
a
UAV
is
defined
as
being
capable
of
controlled,
sustained
level
flight
and
powered
by
a
jet
or
reciprocating
engine.
In
addition,
a
cruise
missile
can
be
considered
to
be
a
UAV,
but
is
treated
separately
on
the
basis
that
the
vehicle
is
the
weapon.
The
acronym
UAV
has
been
expanded
in
some
cases
to
UAVS
(Unmanned
Aircraft
Vehicle
System).
The
FAA
has
adopted
the
acronym
UAS
(Unmanned
1.
1
http://www.theuav.com/

6.
6
Aircraft
System)
to
reflect
the
fact
that
these
complex
systems
include
ground
stations
and
other
elements
besides
the
actual
air
vehicles.
Officially,
the
term
'Unmanned
Aerial
Vehicle'
was
changed
to
'Unmanned
Aircraft
System'
to
reflect
the
fact
that
these
complex
systems
include
ground
stations
and
other
elements
besides
the
actual
air
vehicles.
The
term
UAS,
however,
is
not
widely
used
as
the
term
UAV
has
become
part
of
the
modern
lexicon.
UAV Types
• Target
and
decoy
-­‐
providing
ground
and
aerial
gunnery
a
target
that
simulates
an
enemy
aircraft
or
missile
• Reconnaissance
-­‐
providing
battlefield
intelligence
• Combat
-­‐
providing
attack
capability
for
high-­‐risk
missions
(see
Unmanned
Combat
Air
Vehicle)
• Research
and
development
-­‐
used
to
further
develop
UAV
technologies
to
be
integrated
into
field
deployed
UAV
aircraft
• Civil
and
Commercial
UAVs
-­‐
UAVs
specifically
designed
for
civil
and
commercial
applications.
Degree
of
Autonomy
Some
early
UAVs
are
called
drones
because
they
are
no
more
sophisticated
than
a
simple
radio
controlled
aircraft
being
controlled
by
a
human
pilot
(sometimes
called
the
operator)
at
all
times.
More
sophisticated
versions
may
have
built-­‐in
control
and/or
guidance
systems
to
perform
low
level
human
pilot
duties
such
as
speed
and
flight
path
stabilization,
and
simple
prescript
navigation
functions
such
as
waypoint
following.
From
this
perspective,
most
early
UAVs
are
not
autonomous
at
all.
In
fact,
the
field
of
air
vehicle
autonomy
is
a
recently
emerging
field,
whose
economics
is
largely
driven
by
the
military
to
develop
battle
ready
technology
for
the
war
fighter.
Compared
to
the
manufacturing
of
UAV
flight
hardware,
the
market
for
autonomy
technology
is
fairly
immature
and
undeveloped.
Because
of
this,
autonomy
has
been
and
may
continue
to
be
the
bottleneck
for
future
UAV

7.
7
developments,
and
the
overall
value
and
rate
of
expansion
of
the
future
UAV
market
could
be
largely
driven
by
advances
to
be
made
in
the
field
of
autonomy.
Autonomy
technology
that
will
become
important
to
future
UAV
development
falls
under
the
following
categories:
• Sensor
fusion:
Combining
information
from
different
sensors
for
use
on
board
the
vehicle
• Communications:
Handling
communication
and
coordination
between
multiple
agents
in
the
presence
of
incomplete
and
imperfect
information
• Motion
planning
(also
called
Path
planning):
Determining
an
optimal
path
for
vehicle
to
go
while
meeting
certain
objectives
and
constraints,
such
as
obstacles
• Trajectory
Generation:
Determining
an
optimal
control
maneuver
to
take
to
follow
a
given
path
or
to
go
from
one
location
to
another
• Task
Allocation
and
Scheduling:
Determining
the
optimal
distribution
of
tasks
amongst
a
group
of
agents,
with
time
and
equipment
constraints
• Cooperative
Tactics:
Formulating
an
optimal
sequence
and
spatial
distribution
of
activities
between
agents
in
order
to
maximize
chance
of
success
in
any
given
mission
scenario

8.
8
Understanding the Project
AIM
The
Aim
of
this
project
is
to
design
and
construct
an
Unmanned
Aerial
Vehicle
which
will
be
a
hybrid
between
a
helicopter
and
an
airplane,
so
that
we
can
achieve
advantages
of
both
helicopter
and
airplane.
ABSTRACT
The
purpose
of
this
project
is
to
design
and
construct
a
tilt-­‐rotor
aircraft
with
both
a
vertical
takeoff
and
landing.
The
aircraft
being
a
hybrid
of
airplane
and
helicopter,
which
gives
the
structure
a
superior
performance
and
enhanced
abilities
having
both
the
functions
of
a
helicopter
and
the
aircraft,
which
include
vertical
take-­‐off/landing
and
required
forward
speed.
The
model
aircraft
can
be
constructed
with
balsa
wood
or
any
composite
materials.
The
airframe
consists
of
the
fuselage,
which
is
the
main
component
of
the
airplane,
the
wings(large
section
of
the
aircraft),
and
the
empennage
(tail
section,
or
tail
feathers).
The
components
of
the
wings
and
tail
sections
are
also
known
as
the
control
surfaces
since
they
are
of
course
important
in
controlling
the
airplane.
The
attached
to
the
wings
are
flaps
and
ailerons.
The
empennage
is
the
tail
assembly
consisting
of
the
horizontal
stabilizers,
the
elevators,
the
vertical
stabilizer,
and
the
rudder.
SCOPE
Scope
of
the
project
of
constructing
a
UAV
which
will
possess
the
capabilities
of
both
helicopter
and
airplane.
Many
reasons
to
this
purpose
,
most
important
being
because
this
branch
of
aerospace
industry
has
not
fully
been
succeeded.
Their
success
is
limited
to
jet
aircraft
with
VTOL
which
use
thrust
vectoring
and
helicopters
which
use
cyclic
pitch
and
collective
pitch
to
hover.

9.
9
The
success
of
this
model
could
be
a
breakthrough
for
larger
scale
models
and
eventually
there
could
be
a
new
era
of
transportation
where
the
private,
military
aircrafts
could
also
implement
this
concept
an
use
shorter
runway
for
take-­‐off
and
cruise
at
a
higher
speed.
One
of
the
main
advantages
of
this
type
of
aircraft
is
that
if
in
case
the
engine
fails,
the
aircraft
can
glide
and
land
as
a
normal
aircraft
since
it
has
wings
to
create
lift
unlike
helicopter,
similarly
vice
versa.

10.
10
Parametric Study
The
aircrafts
made
with
the
similar
concept
is
taken
into
this
parametric
study
RC
TWIN
VTOL
PROTOTYPE
Figure
2
Specifications and details
Dimensions
Length
-­‐
43
inches
Wingspan
-­‐
48
inches
Center
wing
-­‐
29
inches
Motor
spacing
-­‐
19
inches

11.
11
Specification
Motors
-­‐
AXI
2212/26
Propellers
-­‐
MPI
MAXX
PRODUCTS
counter
rotating
pair
10
x
4.5
slow
flyer
ESC
controller
-­‐
Castle
Creations
newer
phoenix
25
Amp
with
3
amp
BEC
Batteries
tested
-­‐
Polypus
PQ-­‐2100XP-­‐3S
2100ma
20
C
rated
167
grams
or
PD-­‐B2600N-­‐SP
3S
2600ma
12C
rates
192
grams
External
mixers
-­‐
2
VEE-­‐TAIL
OMNI
mixers
Aircraft
Structure
-­‐
1/4
inch
balsa
tail
and
fuselage,
2
@
8mm
diameter
carbon
fiber
tubes
C
of
G
-­‐
on
the
tilt
spar
tube
of
maximum
1/4
inch
front
of
the
C
of
G
-­‐30%
of
wing
chord
position
WING
Static
Thrust
-­‐
max
1300
grams
Weight
-­‐
920-­‐950
grams

12.
12
V-­‐22
OSPREY
MODEL
Figure
3
2
Specifications and details
Dimension
- Length
–
38.5
inches
- Span
–
36
inches
- Center
wing
–
22
inches
- Weight
–
1500
g
Power
system
–
2
Scorpion
HK
2221-­‐10
motors
Propeller
–
APC
12
x
3.8
slow
flyer
Servos used
- 2
HITEC
HS-­‐5085MG
(for
tilting
motors)
- 2
micro
servos
(for
controlling
movable
surfaces
)
2.
2 2
http://www.theuav.com/

13.
13
Structure
- Primary
–
Balsa
wood
- Secondary
–
Carbon
rods
and
aluminum
pipes
Electricals
- Receiver
–
Futaba
R617FS
- Battery
–
Two
EM2200
4S
- ESC
–
Two
Phoenix
ICE
Lite
50SB
- Gyro
–
Three
Futaba
GY401
- Receiver
power
–
CC
regulator
20A
Pro
Airfoil used
–
NACA
2413
Wing used
–
Straight
wing
Empennage:
Horizontal
and
vertical
stabilizer
–
conventional
Adhesion
- E-­‐poxy
30
minutes
- E-­‐poxy
5
minutes
- Hot
glue

14.
14
Specifications and details (AERO-CHOPPER)
Dimensions
- Length
–
39
inches
- Span
–
34
inches
- Center
wing
–
22
inches
- Approximate
weight
estimation
–
2.5
to
3
kg
Power system
–
two
Power
electric
motors
Propeller
–
APC
12
x
3.8
slow
flyer
Servos used
- 2
high
torque
and
high
speed
servo
(for
tilting
the
motors)
- 4
Micro
servos
(
for
controlling
movable
surfaces
)
Structure
- Primarily
:
Balsa
wood
- Secondary
:
Carbon
rods
and
aluminum
pipes
Electricals
- Minimum
9
channel
receiver
and
transmitter
- Minimum
3
gyros
- 2
external
V-­‐mixer
- Wire
extensions
- Y-­‐splitters
- Two
4cell
battery
packs
- 1
BEC
- 2
Electronic
Speed
Controllers
–
Minimum
60amps
Airfoil used
–
NACA
2414
Wing used
–
straight
single
high
wing
with
uniform
chord

15.
15
Empennage:
Horizontal
and
vertical
stabilizer
–
conventional
Engine
mount
–
is
tilted
inwards
by
2.3degrees
Adhesion
- Z-­‐poxy
30
minutes
- Z-­‐poxy
5
minutes

16.
16
Mission
Objectives
• Design
and
construct
a
hybrid
aircraft
of
a
helicopter
and
an
airplane.
• Ensuring
stable
takeoff,
land
and
transition
from
hover
mode
to
forward
mode.
• Ensure
that
the
aircraft
has
an
average
endurance
of
a
minimum
15
minutes
in
hover
mode
or
normal
mode.
Outcomes
• Gathering
information
about
How
VTOL
mechanism
works.
• The
type
of
wings
and
body
constructed
suitable
to
the
VTOL
concept
• Defining
a
set
of
parameters
that
we
want
the
plane
to
conform
to.
• Identify
the
materials
and
the
budget
required.
• Mathematical
and
aerodynamic
calculations
and
maneuver
calculation.
• Design
the
aircraft
in
a
2D
&
3D
sketch
on
AUTOCAD.
• Create
an
effective
launch
system
in
hover
mode.
• Experiment
the
prototype
model
&
troubleshoot
safety
&
related
issues.
• A
Presentation
of
the
aircraft.
Table
1
SPECIFICATIONS
Wing
span
(A)
Span
<
1m
Type
of
Wing
Straight
wing
Weight
Weight
<
2kg
Fuselage
Length(a)
Length
<
1m

17.
17
GANTT CHART

18.
18

19.
19
DESIGN CONCEPT
The
concept
of
Aero-­‐chopper
is
very
simple
but
involves
sophisticated
electrical
and
mechanics
for
it
to
work.
The
aircraft
will
be
a
twin
engine
and
the
engines
will
be
on
both
the
ends
of
the
wing
and
will
be
placed
exactly
on
the
C.G
of
the
aircraft
so
that
when
the
thrust
is
given,
and
if
the
aircraft
is
balanced
exactly
on
the
C.G(motors),
Aero-­‐chopper
should
lift
vertically.
Figure
4
The
control
of
Aero-­‐chopper
on
the
different
axis
will
be
done
by
moving
the
engines
and
also
by
powering
up
and
down
of
the
motors.
For
the
control
of
the
pitch,
Aero-­‐chopper
will
tilt
its
wing
anti-­‐clockwise
which
would
move
the
direction
of
the
propellers
too.
This
will
cause
a
change
in
the
pitch
of
the
aircraft.

20.
20
Figure
5
The
Aero-­‐chopper
should
also
have
the
capability
to
tilt
its
engine
forward
about
45o
to
help
it
transit
from
Hover
mode
to
normal
aircraft
mode
where
its
engine
will
be
0o
(parallel
to
the
direction
of
flight)
Figure
6

21.
21
COST ANALYSIS
Man hours analysis
Table
2
WBS
Sheet:
1
Analysis
in
hours
Activity
description
Est
to
complete
Est
@
complete
Variance
GANTT
CHART
2
3
1
Research
15
20
5
Aircraft
Design
25
40
15
Design
Approval
3
5
2
Parametric
Design
4
4
0
Airfoil
selection
2
2
0
3D
design
15
20
5
Mission
1
1
0
Selection
of
aircraft
parts
3
5
2
Cost
Analysis
2
2
0
Tools
and
Materials(separate
sheet)
10
16
6
Construction
plan
printing/Tracing
20
23
3
Cutting
of
material
parts
and
organizing
4
4
0
Construction
of
aircraft
structure
accordingly
45
55
10
Assembly
made
rigid
and
Shaping
3
4
1

22.
22
Electricals
and
Servos
purchase(separate
sheet)
5
5
0
Custom
circuit
made
and
tested
4
5
1
Fixing
of
Electricals
and
Servos
10
13
3
Aircraft
performance
test
3
3
0
Performance
calculations
15
20
5
Centre
of
Gravity
placement/calculations
2
2
0
Flight
Test
-­‐
1
3
3
0
Painting
and
finishing
of
aircraft
structure
2
2
0
Flight
Test
-­‐
2
3
4
1
Final
Calculations
2
4
2
Flight
Test
-­‐
3
3
3
0
Project
report
writing
10
15
5
Finalization
of
Aircraft
1
1
0
Deliverable
2
2
0
TOTAL
219
286
67

23.
23
MAN POWER
Table
3
Days
for
the
Project
90
days
Days
devoted
to
the
project
70
days
Average
hours
worked
per
day
4hours/day
Total
hours
for
the
days
worked
45
x
4
=
180
hours
Average
Man
power
=
no.
of
persons/
hours
1/180
So
a
person
has
to
work
for
280
hours
on
this
project.

24.
24
Cost analysis
Table
4
WBS
Sheet:
2
Analysis
in
costs
Activity
description
Est
to
complete
Est
@
complete
Variance
GANTT
CHART
0
0
0
Research
0
30
30
Aircraft
Design
50
70
20
Design
Approval
50
65
15
Parametric
Design
0
0
0
Airfoil
selection
0
0
0
3D
design
0
0
0
Mission
0
0
0
Selection
of
aircraft
parts
0
0
0
Cost
Analysis
0
0
0
Tools
and
Materials(separate
sheet)
600
820
220
Construction
plan
printing/Tracing
50
85
35
Cutting
of
material
parts
and
organizing
30
35
5
Construction
of
aircraft
structure
accordingly
50
60
10
Assembly
made
rigid
and
Shaping
30
30
0

25.
25
Electricals
and
Servos
purchase(separate
sheet)
6000
7740
1740
Custom
circuit
made
and
tested
0
0
0
Fixing
of
Electricals
and
Servos
0
30
30
Aircraft
performance
test
0
0
0
Performance
calculations
0
0
0
Centre
of
Gravity
placement/calculations
0
0
0
Flight
Test
-­‐
1
200
200
0
Painting
and
finishing
of
aircraft
structure
30
40
10
Flight
Test
-­‐
2
200
200
0
Final
Calculations
0
0
0
Flight
Test
-­‐
3
200
200
0
Project
report
writing
0
0
0
Finalization
of
Aircraft
0
0
0
Deliverable
50
50
0
TOAL
7540
9655
2115

26.
26
Cost of materials and electricals
Table
5
Items
Quantity
Cost
per
piece(aed)
Total
Amount
(aed)
Materials
Balsa
wood
pack
1
500
500
Glues
5
35
175
Sand
Paper
10
5
50
Cutter
3
15
45
Monocot
1
50
50
Electricals
Propellers
3
60
180
Electric
Speed
Control
3
480
1440
Battery
3
640
1920
Engine(Motor)
3
460
1380
Radio
unit
1
1000
1000
Landing
Gear
unit
1
500
500
Servo
pack
4
170
680
Servo(Tilt
rotor)
2
290
580
Hinges
pack
3
20
60
Total
43
4225
8560

27.
27
Materials3
Balsa wood
Figure
7
Balsa
wood
is
the
main
material
that
we
have
used
to
construct
the
aircraft.
Balsa
wood
is
lightweight,
inexpensive
and
relatively
strong.
We
have
used
it
to
construct
the
fuselage,
wing
and
tail-­‐plane
as
well
as
in
the
sheeting
of
the
plane.
Ply
wood
Figure
8
We
used
ply
wood
on
our
model
on
the
places
where
we
need
more
strength
like
the
root
rips
of
the
wing,
the
front
side
cover
of
the
fuselage,
servo
plates
etc.
The
materials
that
were
mainly
used
were
Balsa
and
Plywood
3. 3
http://www.moneysmith.net/Soaring/soaring4.html

28.
28
Table
6
Component
Material
Thickness
flat
fuselage
sides,
wing
ribs,
wing
spruces,
main
frame
of
fuselage,
servo
holder,
battery
pack
holder
,
frame
and
landing
gear
support
area
etc.
B-­‐Grain
balsa
wood
4
mm
Elevator
,horizontal
stabilizer,
vertical
stabilizer,
aileron
and
rudder
C-­‐grain
balsa
wood
3.2
mm
Covering
rounded
the
fuselage,
planking
fuselage
and
nose
and
wing
surface
A-­‐grain
1.5
mm
To
support
some
particular
area
like
inside
the
fuselage,
Tilt
roll
of
the
wing,
and
landing
gear
hold
and
support
area
etc.
we
used
very
small
amount
of
ply
wood
to
make
structure
strong.
Plywood
4
mm
Thickness
▬ Mostly
we
used
4mm
balsa
for
our
main
construction
like
wings
,
flat
fuselage
sides,
wing
ribs,
formers,
trailing
edges
where
more
strength
are
required.
▬ We
used
3.2
mm
for
body
where
it
is
not
required
to
be
very
strong
and
it’s
because
to
reduce
weight.
we
also
used
it
for
rudder,
elevator,
stabilizer,
other
attachments
etc.
▬ In
our
project
used
1.5mm
where
it
is
required
for
covering.

29.
29
E-poxy Glue
Figure
9
Epoxy
is
a
strong,
important
modeling
glue
but
one
which
must
be
used
sparingly
because
of
its
heavy
weight.
Epoxy
is
classified
by
its
strength
and
working
time.
Quick
cure,
or
five
minute
epoxy,
is
strong
enough
for
most
modeling
applications,
and
is
very
handy
for
quick
repairs.
Slow
cure
(30
minute
or
more)
epoxy
is
used
when
extra
strength
is
required.
We
have
used
epoxy
to
join
the
major
parts
of
the
airplane.
This
includes
joining
the
wing
mounts
to
the
fuselage,
and
attaching
the
tail
to
the
fuselage.
We
have
also
used
slow
cure
epoxy
for
bonding
the
wood
skins
to
the
foam
wing
and
stabilizer
core.
Masking Tape
Figure
10
We
used
masking
tape
for
minor
repairs
in
the
airplane.
Masking
tape
was
chosen
due
to
its
convenient
size,
shape
and
ease
of
removal.
It
was
mainly
used
for
fixing
small
cracks
in
the
balsa
wood.

30.
30
Tools
Drill tools
Figure
11
We
used
a
small
hand
drill
to
drill
holes
in
the
balsa
wood.
A
drill
press
was
also
used
to
make
sure
that
the
holes
were
straight.
Our
hand
drill
was
able
to
make
holes
of
2mm
thickness.
Protractor
Figure
12
We
used
a
protractor
to
measure
various
angles
in
the
model
aircraft,
which
were
needed
in
the
calculations.
For
example,
we
used
it
to
measure
the
sweptback
angle
and
the
angle
of
the
tail
planes.
Cutter
Figure
13

31.
31
We
used
a
normal
cutter
as
it
was
very
useful
to
cut
the
balsa
wood,
it
easily
cut
through
the
wood
and
was
simple
to
handle.
We
sometimes
used
it
to
file
the
surface
of
the
wood
to
make
it
smooth
and
even.
Rulers
Figure
14
We
used
rulers
for
measuring
the
dimensions
of
the
aircraft
like
wingspan,
length
of
the
fuselage
etc.
Sand paper
Figure
15
Sandpaper
is
used
to
remove
small
quantities
of
material
at
a
time
from
the
surface
of
an
object.
Sandpaper
can
be
used
to
remove
a
specific
material
from
an
object
(such
as
a
layer
of
paint)
or
to
level
and/or
smooth
the
surface
of
the
object.
Sandpaper
comes
in
many
numbered
"grades,"
with
smaller
numbers
being
coarser
and
removing
more
surface
material
with
each
pass.
Higher
numbers
are
finer
and
remove
less
material.
We
have
mostly
used
‘low
grade’
sandpaper
for
polishing
and
smoothing
the
aircraft.
We
have
also
used
it
to
shape
the
ribs
and
spars
of
the
model
aircraft.

32.
32
ELECTRICALS4
MOTORS
Main
wing
motors(2
on
the
either
sides
of
the
wing)
Figure
16
Power
10
Brushless
Out-­‐runner
Motor,
1100Kv
Key Features
• Equivalent
to
a
10-­‐size
glow
engine
for
32–48
ounce
(910–1360
g)
airplanes
• Ideal
for
3D
airplanes
weighing
28–36
ounces
(790–1020
g)
• Ideal
for
models
requiring
up
to
450
watts
of
power
• High-­‐torque,
direct-­‐drive
alternative
to
in-­‐runner
brushless
motors
• Includes
mount,
prop
adapters
and
mounting
hardware
• External
rotor
design—5mm
shaft
can
easily
be
reversed
for
alternative
motor
installations
• Slotted
14-­‐pole
out-­‐runner
design
4. www.e-­‐fliterc.com/Products

33.
33
• High-­‐quality
construction
with
ball
bearings
and
hardened
steel
shaft
• Quiet,
lightweight
operation
Overview
The
Power
10
is
designed
to
deliver
clean
and
quiet
power
for
10-­‐size
sport
and
scale
airplanes
weighing
32
to
48
ounces
(910
to
1360
grams),
3D
airplanes
weighing
28
to
36
ounces
(790
to
1020
grams),
or
models
requiring
up
to
375
watts
of
power.
It’s
an
especially
good
match
for
the
E-­‐flite
Brio
10
for
high
speed
F3A
precision
or
artistic
aerobatics.
Product Specifications
Type:
Brushless
out-­‐runner
motor
Size:
10-­‐size
Bearings
or
Bushings:
One
5
x
14
x
5mm
Bearing,
and
One
5
x
11
x
5mm
Bearing
Wire
Gauge:
16
Recommended
Prop
Range:
10x5–12x6
Voltage:
7.2–12
RPM/Volt
(Kv):
1100
Resistance
(Ri):
.043
ohms
Idle
Current
(Io):
2.10A
@10V
Continuous
Current:
32A
Maximum
Burst
Current:
42A
(15
sec)
Cells:
6–10
Ni-­‐MH/Ni-­‐Cd
or
2–3S
Li-­‐Po
Speed
Control:
35–40A
brushless
Weight:
122
g
(4.3
oz)

34.
34
Overall
Diameter:
35mm
(1.40
in)
Shaft
Diameter:
5mm
(.20
in)
Overall
Length:
43mm
(1.60
in)
Needed
to
Complete
E-­‐flite
Brio
10
40A
ESC
6-­‐
to
10-­‐cell
Ni-­‐MH/Ni-­‐Cd
or
2–3S
Li-­‐Po
10x5
to
12x6
electric
props
Tail
Wing
motor(1
at
the
rear)
Figure
17
Park
370
BL
Outrunner,1200Kv
with
4mm
Hollow
Shaft
Key Features
• Ideal
for
models
requiring
up
to
120
watts
of
power
• Optimized
windings
for
3D
performance

35.
35
• High-­‐torque,
direct-­‐drive
alternative
to
in-­‐runner
brushless
motors
• Includes
mount,
prop
adapters
and
mounting
hardware
• 4mm
hollow
shaft
is
easily
reversed
for
alternative
motor
installations
• Excellent
motor
for
small
3D
airplanes
7–14
oz
(200–400
g)
• Extremely
lightweight—just
1.6
ounces
• Ideal
for
variable
pitch
props
such
as
the
E-­‐flite®
Showstopper
Variable
Pitch
Prop
System
• External
rotor
design
for
better
cooling
• High-­‐quality
construction
with
ball
bearings
Overview
E-­‐flite’s
latest
Park
370
is
a
brushless
out-­‐runner
motor
that
features
a
4mm
hollow
shaft,
ideal
for
use
with
variable
pitch
propellers.
It’s
perfectly
designed
for
electric
models
equipped
with
variable-­‐pitch
propeller
systems,
such
as
the
E-­‐flite®
ShowStopper
VPP
system.
However,
you
don’t
need
a
VPP
to
use
this
motor—it’s
an
excellent
motor
for
small
3D
airplanes
that
weigh
7–
14
ounces.
A
motor
mount,
prop
adapter
and
all
hardware
are
included.
Product Specifications
Type:
Brushless
out-­‐runner
Size:
Park
370
Bearings
or
Bushings:
One
4
x
8
x
4mm
Bearing,
and
One
4
x
9
x
4mm
Bearing
Recommended
Prop
Range:
8x3.8–10x4.7
or
Variable
Pitch
systems
Voltage:
7.2–12V
RPM/Volt
(Kv):
1200
Resistance
(Ri):
.18
ohms
Idle
Current
(Io):
.60A

36.
36
Continuous
Current:
10A
Maximum
Burst
Current:
12A
(15
sec)
Cells:
6–10
Ni-­‐MH/Ni-­‐Cd
or
2–3S
Li-­‐Po
Speed
Control:
12–20A
Brushless
Weight:
45
g
(1.6
oz)
Overall
Diameter:
28mm
(1.10
in)
Shaft
Diameter:
4mm
(.16
in)
hollow
Overall
Length:
25mm
(1.00
in)
Needed
to
Complete
12–20A
brushless
ESC
2–3S
Li-­‐Po
or
6–10
Ni-­‐Cd/Ni-­‐MH
8x3.8–10x4.7
Slow
Flyer
Prop
Variable
Pitch
Prop
option

37.
37
ELECTRONIC SPEED CONTROLLER
ESC
Eletronic
Speed
Control
Detrum
30-­‐40a
2-­‐6s
LIXX
/
5-­‐18s
NC
-­‐
0km
Model:
E
Figure
18
• Model:
ESC-­‐40A
• Size(mm):
50
X
25
X
13
• Weight:
36g
• Current:40A
• NiCd/NiMh]
/servos:
6/5
8/5
10/4
12/3
• [Li-­‐xx]/servos:
2/5
3/4

38.
38
BATTERY
Esky
EK1-­‐0186
20C
11.1v
1800mah
Li-­‐Polymer
battery
Figure
19
Product Description
Table
7
Item
NO.
EK1-­‐0186
Size
100*34*25mm
Weight(g)
47.0ï‫½؟‬ï ‫؟‬½5.0
(single
electric
core)
discharge
magnification
20C
compages
form
connection
in
series
charging
port
XH2.5-­‐4P
reversal
(equilibrium
charge)
Inner
resistance
20mï‫½؟‬ï‫
½؟‬max
(single
electric
core)
discharging
cut-­‐off
voltage
2.75V
(single
electric
core)
charging
cut-­‐off
voltage
4.20ï‫½؟‬ï ‫؟‬½0.05 V
(single
electric
core)
long-­‐time
load
voltage
3.6V~4.1V
(single
electric
core)

39.
39
Radio
JR
Propo
DSX7
7-­‐Channel
2.4GHz
Computer
Radio
Control
System
(DSMJ),
Package
includes
Transmitter
2.4GHz
DSMJ,
RD731
7Ch
2.4G
DSMJ
Receiver
w/EA131
Remote
Receiver,
ES539
Standard
Servo
x3,
TX
8N
1500mah
Ni-­‐MH
battery,
Switch
and
220V
charger.
English
manual
included.
|
Mode
1,
Mode
2
inter-­‐changeable.
Figure
20
Product
Code
:
[DSX7
2.4G
DSMJ
w/ES539
[DSX7JES539]]
Quality
product
from
JR
Propo.
JR
Propo
-­‐
2.4GHz
Spread
Spectrum
Technology
(DSMJ)
JR
Propo
DSX7
2.4GHz
Computer
Radio
Control
System
(DSMJ)
is
suitable
for
Beginner
to
Intermediate
flyers
and
also
the
only
model
for
even
the
advanced.
It
is
reliable
and
stable
with
2.4GHz
with
built-­‐in
system,
promising
an
exciting
flight
in
the
comfort
of
all
flyers.
It
comes
with
Transmitter
2.4GHz,
RD731
2.4GHz
DSMJ
7
Channel
Receiver
w/EA131
remote
receiver,
3pcs
x
ES539
standard
servos
for
electric
model
or
glow
model
use.
The
system
comes
with
Mode
1
which
can
be
changed
to
Mode
2
by
editing
system
software
with
stick
spring.
The
Flight
Mode
is
at
the
right
hand
side.

40.
40
Content
JR
Propo
DSX7
Transmitter
2.4GHz
DSMJ
RD731
7Ch
2.4GHz
DSMJ
Receiver
w/EA131
Remote
Receiver
JR04884
2.4GHz
Remote
wire
extension
(150mm/6")
JR
ES539
Standard
Analog
Servo
x
3pcs
(Servo
Horns
&
mounting
accessories
included)
TX
8N
1500mah
Ni-­‐MH
battery
NEC-­‐322
220V
Tx
&
Rx
charger
Bind
Plug
Set
Switch
2mm
Allen
Wrench
English
manual
included
|
Mode
1
or
Mode
2
inter-­‐changeable.
Spec
-­‐Method:
DSMJ
/
Computer
Mixing
-­‐Number
of
Channels:
7ch
-­‐Transmitter
Weight:
640g
(excluding
battery)
-­‐Battery
fit:
8N1500
-­‐For
Helicopters
or
Airplane
Features
Band:
2.4
GHz
Servos:
ES539
X
3
Receiver:
RD731
(DSMJ)
Transmitter
(Tx)
Battery
Type:
1500mah
Ni-­‐MH
AC:
220V
20-­‐model
memory
Airplane
and
Heli
software
Switch
assignment
P-­‐mixes

41.
41
3-­‐axis
dual
rate
and
expo
3-­‐position
flap
(Airplane)
5-­‐point
throttle
&
pitch
curve
(Heli)
3
flight
modes
plus
hold
(Heli)
Gyro
programming
(Heli)
CCPM
swash
mixing
90/120/180
degree
(CCPM:
Cyclic
Collective
Pitch
Mixing
System)
English
manual
ES539 Standard Analog Servo Specification
Torque:
4.8kg.cm
(66.67oz.in)
Speed:
0.23S/60°
Size:
32.5
x
19
x
38.5mm
(1.28x0.75x1.52in)
Weight:
38g
(1.34oz)

42.
42
Airfoil Selection5
Airfoil
used
–
NACA
2414
As
this
airfoil
seems
to
be
the
most
suited
for
this
application
according
to
the
study
shown
below
Comparing
the
airfoils;
NACA
2412,
NACA2414,
NACA
2414
Naca-­‐2412
Thickness:
12.0%
Max
CL
angle:
15.0
Camber:
2.0%
Max
L/D:
50.702
Trailing
edge
angle:
14.5o
Max
L/D
angle:
5.5
Lower
flatness:
45.2%
Max
L/D
CL:
0.927
Leading
edge
radius:
1.7%
Stall
angle:
7.0
Max
CL:
1.204
Zero-­‐lift
angle:
-­‐2.0
5. 5
http://www.worldofkrauss.com/foils
Figure
21

43.
43
Figure
22
NACA
2414
Figure
23
Thickness:
14.0%
Camber:
2.0%
Trailing
edge
angle:
17.8o
Lower
flatness:
50.5%
Leading
edge
radius:
3.0%
Max
CL:
1.245
Max
CL
angle:
10.5
Max
L/D:
41.542
Max
L/D
angle:
6.0
Max
L/D
CL:
0.943
Stall
angle:
10.5
Zero-­‐lift
angle:
-­‐2.0

44.
44
NACA
2415
Figure
25
Thickness:
15.0%
Camber:
2.0%
Trailing
edge
angle:
19.1o
Lower
flatness:
43.6%
Leading
edge
radius:
3.3%
Max
CL:
1.281
Max
CL
angle:
11.5
Max
L/D:
40.672
Max
L/D
angle:
6.5
Max
L/D
CL:
0.991
Stall
angle:
11.5
Zero-­‐lift
angle:
-­‐2.0

45.
45
Figure
26
From
the
above
figures
NACA
2414
is
the
most
suitable.
NACA
2414
is
selected
since
it
has
good
enough
thickness
to
accommodate
1
cm
rod
for
the
engine
tilting
mechanism.

46.
46
Ribs
shapes
generated
with
the
help
of
the
software
"profili"
Figure
27

47.
47
AIRCRAFT DESIGN
The
2-­‐D
drawing
that
guided
through
the
dimensions
and
construction
process
showing
the
3-­‐
isometric
views
of
the
aircraft.
Top view
Figure
28

48.
48
Side view
Figure
29
Front view
Figure
30

49.
49
Structure designing :(PROFILI)
Wing
structure
with
ribs
placements
designed
with
the
help
of
Profilli
Figure
31

50.
50
Figure
32
Figure
33

51.
51
Rib structure Design on AutoCAD
Wing with ribs placement

52.
52
Fuselage ribs and wing ribs placement
Spars supporting the ribs
Total structure of the wing
Fuselage
ribs
for
support
of
the
structure

53.
53

54.
54
3D Drawing
Side view
Figure
34
Bottom view
Figure
35

55.
55
Top view
Figure
36

56.
56
Circuits
Tilt
rotor
circuit
Figure
37
Figure
38
Tilt
rotor
mechanism
Figure
39
Figure
40

57.
57
Servo
circuit
Figure
41

58.
58
CONSTRUCTION (ASSEMBLY)
Figure
42
The
Design(plan)
gave
us
a
green
signal
to
finally
start
with
the
construction
of
the
aircraft.
The
component
parts
that
were
needed
to
form
an
assembled
aircraft
were
each
traced
and
draw
on
the
balsa
wood
with
the
respective
dimensions
using
the
carbon
paper.
These
designs
of
the
parts
were
traced
with
the
help
of
a
transparent
paper.

59.
59
Figure
43
And
then
all
the
shapes
were
cut
with
the
help
of
a
normal
metal
cutter,
and
then
placed
separately.
Figure
44

60.
60
Starting
with
the
wing,
which
had
the
following
units:
• 8
airfoil
shaped
ribs
each
wing.
• 3
spars
• Tilt
rotor
holder
ribs
Figure
45
Figure
46
Figure
47

61.
61
Holes
made
with
the
help
of
a
small
drilling
machine
done
by
a
professional.
Holes
made
for
the
space
provision
of
the
spars
going
through
the
airfoil
parts.
Figure
48
Wing
placed
according
to
the
design
with
the
spars
going
through
them
making
the
entire
inner
structure
of
the
wing.

62.
62
Fuselage
Figure
49
The
Fuselage
ribs
cut
accordingly
and
shaped
as
per
the
design.
Figure
50
Figure
51
Figure
52

63.
63
Figure
53
Spaces
at
the
sides
of
the
fuselage
ribs
provided
for
placement
of
the
support
balsa
sticks
making
the
fuselage
structure
rigid.
Figure
54
The
fuselage
ribs
placed
accordingly
at
correct
distances
as
per
the
design.
Long
balsa
sticks
glued
to
the
spaces
provided
at
the
sides
of
the
fuselage
ribs.

64.
64
Figure
55
Figure
56
The
center
part
of
the
wing
where
it
is
placed
on
top
of
the
fuselage
structure,
is
constructed
accordingly
for
the
holding
of
the
tilt
rotor
mechanism
parts.

65.
65
Figure
57
Ply
wood
used
for
the
support
of
the
wing
structure
against
the
fuselage
to
give
the
area
a
better
rigidness
and
support,
and
a
free
movement
in
direction
for
the
wing.
Figure
58
Landing
gear
support
is
constructed
at
the
lower
part
of
the
fuselage
on
the
either
sides,
so
as
to
give
the
landing
gear
a
space
away
from
the
main
fuselage
structure.

66.
66
Engine Mount
Figure
59
The
engines
placed
on
the
either
sides
of
the
wing
must
be
supported
very
strong
as
high
stress
is
faced
in
this
area
due
to
maximum
throttle
of
the
motor.
This
area
is
mounted
with
balsa
and
ply
wood
together
giving
it
a
very
good
hold
preventing
from
breaking
due
to
stress.
Figure
60

67.
67
Tail wing
Figure
61
The
tail-­‐wing
includes
the
horizontal
stabilizer
,
the
rudder
and
the
tail
motor
mount.
Figure
62
Parts
of
the
tail
wing
placed
and
fixed
accordingly
forming
the
internal
structure
of
the
horizontal
stabilizer
and
the
rudder.

68.
68
Figure
63
The
total
internal
structure
is
constructed.
Figure
64
Figure
65

69.
69
Tilt-Rotor mechanism structure
The
tilt
rotor
section,
constructed
accordingly
with
the
provision
of
the
spar
going
through
the
whole
wing
and
the
strong
support
for
the
tilt
rotor
mechanism
structures.
Figure
66
Figure
67
Figure
68
Figure
69

70.
70
Figure
70
Wing
at
the
tilt
position
for
the
hovering
part
of
flight
Electricals
and
servos
fixed
at
the
appropriate
locations
Figure
71
Figure
72

71.
71
Tail-­‐motor
fixed
with
the
mount
supporting
it
and
giving
the
propeller
blades
a
clearance
distance
from
the
tail
wing.
Figure
73
Figure
74
Figure
75
Landing
gear
attached,
one
on
either
sides
and
one
at
the
tail-­‐part
of
the
fuselage
Figure
76

72.
72
Battery
holder
is
made
by
creating
a
space
exactly
measured
for
the
battery
to
fit
it.
Figure
77
Motors
fixed
to
the
mounts
on
the
either
side
of
the
wings.
Figure
78

73.
73
Tilt-­‐Rotor
Aircraft
sheeting,
shaped
and
painted.
Figure
79
Aero-­‐chopper
presented
with
the
Tilt-­‐rotor
function.
Figure
80

74.
74
GRAPHS6
The
graphs
that
we
are
going
to
use
are
the
following
The
aerodynamic
form
factor
graph
Figure
81
6. 6
Fundamentals
of
Flight
by
Richard
S
Shovel

75.
75
Figure
82
Figure
83
7

76.
76
Figure
84
Figure
85

77.
77
Table
8

78.
78
Area Calculation
CALCULATIONS:
Wing
Drawing
1
Drawing
2
Rectangle
Area
=
l
x
b
=
35
x
18
=
648cm2
RIGHT
+
LEFT
=
648
+
648
=
1296cm2

79.
79
Drawing
3
Rectangle
Area
=
l
x
b
=
13.5
x
9.1
=
122.85cm2
Total
wing
area(TOP)
=
Left
section
+
Right
section
+
Center
section
=
648
+
648
+
122.85
=
1418.85cm2
Total
wing
area(BOTTOM)
=
Total
wing
area(TOP)
Total
Wing
Area(TOP
and
BOTTOM)
=
TOP
+
BOTTOM
=
1418.85cm2
+
1418.85cm2
=
2837.7cm2
Airfoil shaped side section of wing
With
the
help
of
AutoCAD
the
exact
area
of
the
side
section
of
the
wing
could
be
taken
by
calculating
the
area
of
the
airfoil.

80.
80
Drawing
5
Area
=
4.1455inch2
=
26.745cm2
2
sides
=
26.745cm2
x
2
=
53.49cm2
Area
of
the
sides
view
of
the
wing
=
53.49cm2
Total
surface
Area
of
the
Wing
=
Side-­‐view
Area
+
Top
&
Bottom
view
Area
=
53.49cm2
+
2837.7cm2
=
2891.19cm2
Total
Surface
Area
of
the
Wing(MAIN)
=
2891.19cm2
Drawing
4

81.
81
Horizontal Stabilizer
Drawing
6
Rectangle
Area
=
l
x
b
=
7.5
x
12.2
=
91.5cm2
Triangle
Area
=
1/2
b
h
=
1/2
x
4.5
x
12.2
=
27.45cm2
Total
=
Rectangle
+
Triangle
=
27.45
+
91.5
=
118.95cm2
2
sides
=
118.95
+
118.95
=
237.9cm2

82.
82
Vertical Stabilizer
Drawing
7
Rectangle
Area
=
l
x
b
=
52
x
10
=
520cm2
Top
and
bottom
=
520
x
2
=
1040cm2
Total
Area
=
1040cm2
Engine Mount
Drawing
8
l
=
11.7cm

83.
83
w
=
5.1cm
h
=
5.1cm
Area
of
cuboid
=
2
(
lw
+
wh
+
hl
)
=
2
(
11.7x5.1
+
5.1x5.1
+
5.1x11.6
)
=
2
(145.35)
=
290.7cm2
Total
Area
of
Engine
Mount(2
sides)
=
290.7cm2
x
2
=
581.14cm2
Engine Mount(TAIL)
Drawing
9
l
=
11.5cm
,
w
=
3.8cm
,
h
=
2cm
Area
of
cuboid
=
2
(
lw
+
wh
+
hl
)
=
2
(
11.5x3.8
+
3.8x2
+
11.5x2
)
=
2(
74.3
)
=
148.6cm2
Total
Area
of
Engine
Mount(TAIL)
148.6cm2

84.
84
Fins
Drawing
10
Triangle
Area
=
1/2
b
h
=
1/2
x
4.9
x
6.8
=
1/2
x
33.32
=
16.66cm2
Rectangle(R1)
Area
=
l
x
b
=
6.8
x
5
=
34cm2
Rectangle(R2)
Area
=
l
x
b
=
9.9
x
2
=19.8cm2
Total
Area(one
side-­‐one
fin)=Triangle
+
R1
+
R2
=
16.66
+
34
+
19.8
=
70.46cm2
2
Sides
=
70.46
x
2
=
140.92cm2
;
2
Fins
=
140.92
x
2
=
281.84cm2
Total
Area
of
the
fins
=
281.84cm2

85.
85
Landing Gear Hold
Drawing
11
Airfoil
area
-­‐
2.7910cm2
=
Side
surface
53.49
-­‐
2.7910
=
50.699
Area
=
50.699cm2
Forward section
Drawing
12
Area
=
l
x
b
=
7.5
x
2
=
15cm2

86.
86
Top and Bottom surface
Drawing
13
Area
=
l
x
b
=
7.5
x
16
=
120cm2
Top
and
bottom
=
120
x
2
=
240cm2
Total
Landing
gear
hold
Area
=
Side
+
Forward
+
Top
and
Bottom
=
50.699
+
240
+15
=
305.699cm2

87.
87
Area of Fuselage
Drawing
14
Area
of
the
fuselage
side
section
=
Area
A
+
Area
B
+Area
C
+
Area
D
+
Area
E
+
Area
F
Area
A
(Trapezium)
Drawing
15
Area
of
Trapezium
=
(a
+
b)/2
x
h
=
(5
+
6.3)/2
x
2.9
=
16.385cm2

88.
88
Area
B
Drawing
16
Area
of
Trapezium
=
(a
+
b)/2
x
h
=
(6.3
+
8.5)/2
x
4
=
29.6cm2
Area
C
Drawing
17
Rectangle
Area
=
l
x
b
=
56.95cm2
Triangle
Area
=
1/2
x
b
x
h
=
1/2
x
4.6
x
6.7
=
15.41cm2
Total
Area
=
56.95
+
15.41
=
72.36cm2

89.
89
D
Drawing
19
Can
be
assumed
as:
Area
=
l
x
b
=
13.4
x
16.5
=
221.1cm2
E
Drawing
20
Drawing
18

90.
90
Rectangle
Area
=
l
x
b
=
7.8
x
23.2
=
180.96cm2
Triangle
Area
=
1/2
x
b
x
h
=
1/2
x
5.9
x
23.2
=
249.4cm2
F
Drawing
21
Area
=
1/2
x
b
x
h
=
1/2
x
7.8
x
24.3
=
94.77cm2
Total
Area
of
Fuselage
Side
section
=
A
+
B
+
C
+
D
+
E
+
F
=
16.385
29.6
+
72.36
+
221.1
+
249.4
+
94.77
=
683.615cm2
Both
sides
=
683.615
+
683.615
=
1,367.23cm2

91.
91
Fuselage(TOP AND BOTTOM)
Drawing
22

92.
92
A'
Drawing
23
Area
of
trapezium
=
(
a
+
b
)/2
x
h
=
(
6.2
+
12.1
)/2
x
6
=
225.06cm2
B'
Drawing
24
Area
of
Trapezium
=
(
a
+
b
)/2
x
h
=
(
12.1
+
13
)
/
2
x
7.6
=
95.38cm2

93.
93
C'
Drawing
25
Area
=
l
x
b
=
13
x
10
=
130cm2
D'
Drawing
26
Area
=
l
x
b
=
8.2
x
5.5
=
45.1cm2

94.
94
E'
Drawing
27
Area
=
l
x
b
=
13
x
29.4
=
382.2cm2
F'
Drawing
28
Area
=
1/2
x
b
x
h
=
1/2
x
13
x
24
=
156cm2

95.
95
Total Area of Fuselage(TOP)
Area
A'
+
B'
+
C'
+
D'
+
E'
+
F'
=
Total
Area
225.06
95.38
+
130
+
45.1
+
382.2
+
156
=
1,033.74cm2
TOP
and
BOTTOM
=
1033.74
x
2
2067.48cm2
Front
surface
Drawing
29
Area
=
l
x
b
=
6.2
x
5
=
31cm2
Total
Area
of
Fuselage
SIDES
+
TOP/BOTTOM
+
FRONT
=
1367.23
+
2067.48
=
3465.71cm2
Total
Area
of
Fuselage
=
3465.71cm2
Total
Area
of
Wing
=
2891.19cm2
Total
Area
of
Tailing
=
1040cm2
Total
Area
of
Horizontal
Stabilizer
=
237.9cm2

96.
96
Total
Area
of
Fins
=
281.84cm2
Total
Area
of
Engine
Mounts(MAIN)
=
581.14cm2
Total
Area
of
Engine
mount(TAIL)
=
148.6cm2
Total
Area
of
Landing
Gear
Hold
=
305.699cm2
TOTAL SURFACE AREA OF THE AIRCRAFT =
Fuselage
+
Wing
+
Tailing
+
Horizontal
Stabilizer
+
Fins
+
Engine
Mounts(MAIN)
+
Engine
mount(TAIL)
+
Landing
Gear
Hold
=
3465.71cm2
+
2891.19cm2
+
1040cm2
+
237.9cm2
+
281.84cm2
+
581.14cm2
+
148.6cm2
+
305.699cm2
Total
Surface
Area
of
the
Aircraft
=
8952.079cm2

97.
97
PERFORMANCE ANALYSIS
LIFT
Airfoil
used
is
NACA
2414
The
software
profili
gives
us
the
following
values;
CLmax
=
1.379
at
15o
AOA
CL
=
0.752
at
4o
AOA
During cruise
Considering
the
angle
of
attack
of
wing,
during
cruising
will
be
40
.
We
know
that
L
=
W
during
cruise.
L
=
2
KG
L
=
20
N
Ρ(density)
at
sea
level
=
1.225
kg/
m3
S(wing
area)
=
0.05898m2
L
=
1/2
P
CL
V2
S
Eq
(1)
V2
=
2L
/
ρ
CL
S
=
2
*
20
/
1.225
*
0.752
*
0.05898
V2
=
737.2
V
=
27.15m/s

98.
98
During Landing
The
Cl
is
at
max
=
1.379
V2
=
2L
/
ρ
CL
S
=
2
*
20
/
1.225
*
1.379
*
0.0589
V2
=
409.50
V
=
20.2
m/s

99.
99
Vstall
is
the
lowest
speed
at
which
steady
controllable
flight
can
be
maintained
any
further
increase
in
AOA
will
cause
flow
separation
on
the
wing
upper
surface,
a
drop
in
lift,
a
large
increase
in
drag.
In
a
well-­‐designed
airplane,
a
strong
pitch-­‐down
moment
is
experienced.
Vstall
=
Vat
landing
Vstall
=
20.2
m/s
LIFT
during
landing
L
=
1/2
P
CL
V2
S
Eq
(1)
=
1/2
*1.225*
1.379*20.22
*
0.05898
L
=
20.2
N
During
take
off
Velocity
at
take-­‐off
is
20%
greater
than
Vstall.
VTO
=
20.2
+
20.2
x
0.20
=
24.24
m/s

100.
100
OR
Around
70%
of
CLMAX
i.e.
0.70x1.379
=
0.966
VTO
2
=
2L
/
ρ
CL
S
=
2
*
20
/
1.225
*
0.966
*
0.05898
i.e.
At
60
AOA
VTO
=
23.9
m/s
LIFT during Take-off
LTO
=
1/2
P
CL
V2
S
Eq
(1)
[since
CL
=
0.966
=
1/2
*1.225*
0.966*20.22
*
0.05898
and
VTO
=
21.8]
LTO
=
14.43N
DRAG
The
total
Drag
of
the
Aircraft
is
calculated
by
summing
the
parasite
and
induced
drag
together.

101.
101
CD
=
CDP
+
CDi
D
=
CDqS
Drag
is
calculated
for
three
phase
of
flight
i.e.
Take
off,
Cruise
and
landing.
At Take Off
CDptotal
is
calculated
by
computing
CDp
for
wing,
fuselage
,
horizontal
and
vertical
stabilizer
separately.
CDp
of
wing
∑
𝐾𝐶fswet
/
Sref
Eq
(4)
Sref
=
0.028912m3
Swet
=
0.05898
m3
Cr
=
0.18
m
CT
=
0.18
m
σ
=
CT
/
Cr
=
1
L
=
MAC
Eq
(5)
=
2/3
x
Cr
(1
+
σ
-­‐
σ/(1
+
σ)
)
=
2/3
*
0.18
(
1
+
1
-­‐
1/(1
+
1))
=
2/3
*0.18(2
-­‐
1/2)
=
0.18
L
=
0.18

102.
102
V
=
1.4607 * 10-5
RN
=
V0
x
L/v
Eq
(6)
=
24.24
*
0.18
/
1.4607
*
10-­‐5
RN
=
298,706.0998
Since
RN
>
200,000
The
flow
is
turbulent
Cf
for
turbulent
Cf
=
0.455
/
[(log10RN)2.58
=
0.455
/
[log10298,706.0998)
2.58
=
5.6
x
10-­‐3
Eq
(7)