complete ppt.ppsx

(1)

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ANSTINE MATHEW AUGUSTINE ANSTINE MATHEW AUGUSTINE (32208101006) (32208101006) ARUN KRISHNAN. U ARUN KRISHNAN. U (32208101009) (32208101009) MAHESH. J MAHESH. J (32208101029) (32208101029) VETRI SELVAN. S VETRI SELVAN. S (32208101057) (32208101057)

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(3)



_{Military aircraft designed to attack ground}

and sea target by dropping bombs on

them.



Strategic bombers are designed for long-

Strategic bombers are designed for

long-range bombing missions against strategic

range bombing missions against strategic

targets to damage enemy nations war

effort

(4)



_{Light bombers}



_{Medium bombers}



_{Dive bombers}



_{Fighters bomber}



_{Ground attack aircraft}



_{Multi role combat}

aircraft

(5)

Major type of aircraft

designs

•

Conceptual design

•

Preliminary design

•

(6)

Conceptual design

•

• It depends on what are the major factors for designingIt depends on what are the major factors for designingIt depends on what are the major factors for designingIt depends on what are the major factors for designing

the aircraft.

the aircraft. the aircraft.

•

• (a) Power plant Location:(a) Power plant Location:(a) Power plant Location:(a) Power plant Location: •

• The Power plant must be located The Power plant must be located in the wings.The Power plant must be located in The Power plant must be located in in the wings.the wings.the wings. •

• (b) Selection of Engine:(b) Selection of Engine:(b) Selection of Engine:(b) Selection of Engine: •

• The engine should be selected according The engine should be selected according to the power The engine should be selected according to The engine should be selected according to to the power the power the power

required i.e., thrust required.

required i.e., thrust required. required i.e., thrust required.

•

• (c) Wing selection:(c) Wing selection:(c) Wing selection:(c) Wing selection: •

• The selection of wing depends upon the selection of The selection of wing depends upon the selection of The selection of wing depends upon the selection of The selection of wing depends upon the selection of •

• (1) Low wing(1) Low wing(1) Low wing(1) Low wing •

• (2) Mid wing(2) Mid wing(2) Mid wing(2) Mid wing •

• (3) High wing(3) High wing(3) High wing(3) High wing

- For a bomber the wing is mostly high wing

- For a bomber the wing is mostly high wing - For a bomber the wing is mostly high wing configuration and anhedral.

configuration and anhedral.

configuration and anhedral. configuration and anhedral.

- Sweep may be required in order to reduce

- Sweep may be required in order to reduce - Sweep may be required in order to reduce wave drag.

wave drag.

wave drag. wave drag.

(7)

2. Preliminary design:

Preliminary is based upon number of

factors like Loitering.

3. Detailed design:

In the detailed design considers each & every

rivets, bolts, paints etc. In this design

the

rivets, bolts, paints etc. In this design

rivets, bolts, paints etc. In this design the

the

connection & allocations are made.

(8)



_{To design a bomber aircraft}



_{Range of 20000 km & must carry 75000 kg+}

of bombs & missiles.



_{At supersonic & subsonic regimes}



_{To operate at regional bases with low cost of}

operation & maintenance



_{The aircraft must also be capable of single}

pilot operation scenario.



_{Due to long range pilot work load must be}

reduced



_{The aircraft must be all weather , all terrain}

operation capable including the airbase.



_{To take up a load factor +8g to +7.5g to}

-3.5g.

(9)

•

Collect data of existing aircraft of similar

purpose i.e., bomber.

•

The basic factors of aircrafts performance

viz. Weight, Cruise velocity ,Range ,Wing

area & Engine thrust.

•

The performance data of various bomber

aircraft with payload capacity between 5000

& 56600 kg was collected.

(10)

•

Mirage IIIE

•

Mirage IVA

• •

F-111F

• •

F-111F swept

• •

Tu-22R

• •

Tu-85/1

• •

YB-60

•

(11)

Preferred

Configuration:

(12)

rom

Comparison

_Parameters

•

• Max takeoff weight (kg)Max takeoff weight (kg) •

• Thrust to weight ratio Thrust to weight ratio •

• Aspect ratioAspect ratio •

• Wing loading (N/sq.m)Wing loading (N/sq.m) •

• Span to height ratioSpan to height ratio •

• Span to length ratioSpan to length ratio •

• Combat radius (km)Combat radius (km) •

• Pay load capacity (kmph)Pay load capacity (kmph) •

• Max Speed (kmph)Max Speed (kmph) •

• Service ceiling (m)Service ceiling (m) •

• Max Speed (m/s)Max Speed (m/s)

Values

• •

500000

• •

0.28

• •

8.4

• •

7848

• •

5

• •

1.5

• •

5000

• •

75000

• •

1000

• •

15000

• •

277.77

(13)

(14)

General rough

G

Ge

en

ne

erra

a rro

ou

ug

g

estimate

(15)

(16)

Mass Fraction

Payload

0.15

0.15 Fuel

Fuel

0.45

0.45 Structure

Structure

0.32

0.32 Power plant

Power plant

0.07

0.07 Fixed equipments

Fixed equipments

0.01

0.01 Total

Total

1.00

(17)

Redefined Mass

Estimation

2’ 2’ 3’ 3’ 4’4’ 5’5’ 6’ 6’ 7’7’ 8’ 8’ 9’ 9’ 10’10’ 0 0 11 R R 3 3 2 2 h h 10000 km 10000 km 1000 km 1000 km 1000 km 1000 km 9000 km 9000 km 1/2 hr 1/2 hr

Mission profile for Strategic bombing

(18)

(19)

Analysis of mission

profile

TSFC values for Bomber

Cruise

Cruise LoiterLoiter

0.5

(20)

(21)

Comparative data of

Engines

(22)

Engine Selection

N Naamme e oof f tthhe e EEnnggiinnee GGPP--77000000 Manufacturer

Manufacturer Engine AllianceEngine Alliance

Type

Type Turbofan 2 Shaft Turbofan 2 Shaft Length (m) Length (m) 4.744.74 Diameter (m) Diameter (m) 3.163.16 Wet weight (kg) Wet weight (kg) 68006800 Dry Weight (kg) Dry Weight (kg) 67126712 Maximum Thrust (kN) Maximum Thrust (kN) 363363

Overall Pressure Ratio

Overall Pressure Ratio 43.943.9

Thrust to Weight Ratio

Thrust to Weight Ratio 4.734.73

Fan Diameter (m)

Fan Diameter (m) 2.952.95

The

above

engine

has

been s

elected fro

m

a

list

The

(23)

Redefined Thrust to

weight ratio

(24)

AIRFOIL SELECTION

(25)

content

•

Airfoil nomenclature

•

Lift coefficient

•

Drag coefficient

•

Types of airfoil

•

Formula used

•

(26)

AIRFOIL NOMENCLATURE



The

cross-section

shape

obtained

by

the intersection of wing with the

perpendicular plane is called airfoil.



_{The major design feature of an airfoil}

is

the

mean

chamber

line

,which

is

the

locus

of

points

halfway

between

the

upper and lower surface ,as measured

perpendicular

to

mean

chamber

line

itself

.



The

most

forward

and

rearward

points

of

(27)

(28)



_{THE FORWARD AND REARWARD POINTS OF THE}

MEAN CAMBER LINE ARE THE

LEADING AND TRAILING EDGES.



CHORD LINE

THE STRAIGHT LINE CONNECTING THE LEADING &

TRAILING EDGES.



MEAN CAMBER LINE

THE LINE BETWEEN UPPER &LOWER SU

THE LINE BETWEEN UPPER &LOWER SURFACES.

RFACES.



_CHAMBER

MAXIMUM DISTANCE BETWEET THE MEAN

CAMBER LINE & THE CHORD LINE

(29)

LIFT COEFFICIENT

•

The lift coefficient (

C

LL

or C

Z Z

) is a

) is a dimensionless

dimensionless

coefficient that relates the lift generated by an

aerodynami

aerodynamic body such as

c body such as a wing or complete

a wing or complete

aircraft, the dynamic pressure of the fluid flow

around the body, and a reference area

associated with the body. It is also used to refer

to the aerodynamic lift characteristics of a 2D

airfoil section, whereby the reference "area" is

taken as the airfoil chord. It may also b

taken as the airfoil chord. It may also be

e

described as the ratio of lift pressure to dynamic

(30)

Drag Co-efficient:

The drag coefficient (commonly denoted as

Cd, Cx or Cw) is a dimensionless quantity

that is used to quantify the drag or

resistance of an object in a fluid environment

such as air or water. It is used in the drag

equation, where a lower drag coefficient

indicates the object will have less

aerodynamic or hydrodynamic drag. The

drag coefficient is always associated with a

particular surface area.

(31)

TYPES OF AIRFOIL

•

CHAMBERED AIRFOIL

•

(32)

CHAMBERED AIRFOIL

•

It is also called as unsymmetrical airfoil .

•

Upper surface of the airfoil is not equal to

lower surface.

SYMMETRICAL AIRFOIL:

•

Surface above the chord line and below

the chord line are equal.

(33)

(34)

FORMULA USED

(35)

FORMULA USED

(36)

(37)

6. Airfoil selection and Wing

Geometry estimates

•

Main Parameter Selection:

•

(38)

(39)

(40)

Thickness based Reynolds

Number

Flap selection:

(41)

Wing geometry

(42)

Critical Mach number for the

airfoil

(43)

(44)

LANDING GEAR

TYRE SELECTION

•

Load Distribution

•

Typical load of aircraft while landing ;W

LLLL

=W

T T T T

-O.8W

FFFF

•

While aborting mission ; W

LLLL

=W

T T T T

-O.1W

FFFF

•

(45)

(46)

CONTACT AREA

• •

Ww=Ap x P

• •

Ap=2.3 √ d

ww

w

ww

(dw/2-Rt)

• •

Rt=(dw/2-Ap/(2.3 √d

ww

w

ww

))

*RUN WAY LOADING

Runway loading=load on each wheel/area of

contact

(47)

Runway Loading

(48)

DIMENSIONAL ESTIMATES

•

Span to height ratio=b/ha ≈5

•

Span to length ratio=b/la ≈ 1.5

•

CONFIGARATION OF TAIL

•

Horizontal stabilizer

•

Horizontal stabilizer sizing 15%

Horizontal stabilizer sizing 15% of wing

of wing area;sh/s=0

area;sh/s=0.15

.15

•

Vertical stabilizer geometry

•

(49)

Configuration of

tail

(50)

Airfoil NACA 0012

(51)

(52)

•

PREPARATION OF LAY OUT

•

Wing location and C.G

Wing location and C.G estimation

estimation

W

fuselage X fuselage + W wing (X +X

wing) = (Wfuselage+Wwing) (X+Xfinal)

•

Where X is the location of wing

Where X is the location of wing root

root

L.E from the nose fuselage and Xfinal is

the reaction of cg from the L.E at root

•

(53)

Wing Detail for cg

estimation

(54)

Three views of

Aircraft

(55)

Front view

(56)

Side view

(57)

(58)

(59)

DRAG POLAR DRAG POLAR

•

Drag equation for entire

Aircraft:Cd=Cdwing+Cdothers+KCL^2

•

*wetted surface area

•

Fuselage

Fuselage =Wfuselage*hfusel

=Wfuselage*hfuselage

age

•

Engine =4* π/4d^2

•

Nose landing gear=dwWw4

•

Main landing gear=dwWw12

•

Main landing gear=dwWw8

Flap=Lflap * Wflap

(60)

•

Take off performance

=Cd

permanent

+Cd

LGLG

+Cd

flapflap

+Cd

wingwing •

•

Landing

performance=Cd

permanentpermanent

+Cd

LGLG

+Cd

flapflap

+Cd

wing

•

(61)

Drag polar

(62)

Lift to Drag Ratio

(63)

Performance

Calculations

•

Thrust required and Thrust available

analysis:

•

W

11

= 25% of Fuel and 100

= 25% of Fuel and 100 % of Payload

% of Payload

•

W

11

= 3185533.292 N

•

W

22

= 50% of Fuel and 100

= 50% of Fuel and 100 % of Payload

% of Payload

•

W

22

= 3784962.23 N

•

W

33

= 75% of Fuel and 100

= 75% of Fuel and 100 % of Payload

% of Payload

•

(64)

Thrust scenarios at Sea level for

different weights

(65)

Thrust scenarios at 11 km altitude for

different weights

(66)