Conceptual Aircraft Design (eBook)

An Industrial Approach

Ajoy Kumar Kundu, Mark A. Price, David Riordan (Autoren)

eBook Download: EPUB

2018
John Wiley & Sons (Verlag)
978-1-119-50026-1 (ISBN)

Infos

Provides a Comprehensive Introduction to Aircraft Design with an Industrial Approach 

This book introduces readers to aircraft design, placing great emphasis on industrial practice. It includes worked out design examples for several different classes of aircraft, including Learjet 45, Tucano Turboprop Trainer, BAe Hawk and Airbus A320. It considers performance substantiation and compliance to certification requirements and market specifications of take-off/landing field lengths, initial climb/high speed cruise, turning capability and payload/range. Military requirements are discussed, covering some aspects of combat, as is operating cost estimation methodology, safety considerations, environmental issues, flight deck layout, avionics and more general aircraft systems. The book also includes a chapter on electric aircraft design along with a full range of industry standard aircraft sizing analyses.

Split into two parts, Conceptual Aircraft Design: An Industrial Approach spends the first part dealing with the pre-requisite information for configuring aircraft so that readers can make informed decisions when designing vessels. The second part devotes itself to new aircraft concept definition. It also offers additional analyses and design information (e.g., on cost, manufacture, systems, role of CFD, etc.) integral to conceptual design study. The book finishes with an introduction to electric aircraft and futuristic design concepts currently under study.

• Presents an informative, industrial approach to aircraft design
• Features design examples for aircraft such as the Learjet 45, Tucano Turboprop Trainer, BAe Hawk, Airbus A320
• Includes a full range of industry standard aircraft sizing analyses
• Looks at several performance substantiation and compliance to certification requirements
• Discusses the military requirements covering some combat aspects
• Accompanied by a website hosting supporting material

Conceptual Aircraft Design: An Industrial Approach is an excellent resource for those designing and building modern aircraft for commercial, military, and private use.

Dr. Ajoy Kumar Kundu, PhD, FRAeS, FIMechE, CEng, is a former Professor (IIT, Kharagpur), Chief Aircraft Designer (HAL) and retired from Bombardier, Belfast. He is current honorary visiting faculty member in the School of Mechanical and Aerospace Engineering (QUB). He held private pilot licence.

Professor Mark A. Price, PhD, CEng, FRAeS, FIMechE, is Pro-Vice-Chancellor for the Faculty of Engineering and Physical Sciences at Queen's University Belfast (QUB).

David Riordan, MSc, CEng, is Engineering Fellow, Nacelle Design and Powerplant Integration at Bombardier, Belfast, having previously been Chief Technical Engineer.

Textauszug

List of Symbols and Abbreviations

Symbols

A

area

A1

intake high light area

APR

Augmented power rating

Ath

throat area

AW

wetted area

AR

aspect ratio

a

speed of sound, acceleration

ā

average acceleration at 0.7 V2

ac

aerodynamic centre

a0_w

wing zero lift line relative to fuselage reference line

αht

angle of attack at the H‐tail

b

span

CR, CB

root chord

CD

drag coefficient

CDi

induced drag coefficient

CDp

parasite drag coefficient

CDpmin

minimum parasite drag coefficient

CDw

wave drag coefficient

Cv

specific heat at constant volume

CF

overall skin friction coefficient, force coefficient

Cf

local skin friction coefficient, coefficient of friction

CL

lift coefficient

Cl

sectional lift coefficient, rolling moment coefficient

CLi

integrated design lift coefficient

CLα

lift curve slope

CLβ

side slip curve slope

Cm

pitching moment coefficient

Cn

yawing moment coefficient

Cp

pressure coefficient, power coefficient, specific heat at constant pressure

CT

thrust coefficient

CHT

horizontal tail volume coefficient

CVT

vertical tail volume coefficient

Cxxxx

cost with subscript identifying parts assembly

C′xxxx

cost heading for the type

CC

combustion chamber

CG

centre of gravity

c

chord

croot

root chord

ctip

tip chord

cp

centre of pressure

D

drag, diameter

Dskin

skin friction drag

Dpress

pressure drag

d

diameter

E

modulus of elasticity, stored energy

E*

mass (gravimetric) specific energy,

EV*

volumetric specific energy density

e

Oswald's factor

εu

deflected upwash angle

εd

deflected downwash angle

F

force

f

flat plate equivalent of drag, wing span

fc

ratio of speed of sound (altitude to sea level)

Fca

aft fuselage closure angle

Fcf

front fuselage closure angle

FB

body axis

FI

inertia axis

FW

wind axis

Fxxx

component mass fraction, subscript identifies the item (Section 8.8)

F/ma

specific thrust

FR

fineness ratio

G

gearing ratio

g

acceleration due to gravity

H

height

h

vertical distance, height

if

incidence of the fuselage camber line relative to fuselage reference line

it

angle between H‐tail MACHT and fuselage reference line

iw

wing and fuselage setting angle.

J

advance ratio

k

constant, sometimes with subscript for each application

L

length, lift

LFB

nacelle fore‐body length

LN

nacelle length

LVT, lVT

vertical tail arm

LHT, lHT

horizontal tail arm

L

length

M

mass, moment

Mf

fuel mass

Mi

component group mass, subscript identifies the item (Section 8.6)

Mxxx

component item mass, subscript identifies the item (Section 8.6)

m

mass

air mass flow rate

fuel mass flow rate

primary (hot) air mass flow rate (turbofan)

secondary (cold) air mass flow rate (turbofan)

N

revolution per minute, number of blades, normal force

Ne

number of engine

n

load factor

ng

load factor times acceleration due to gravity

P, p

static pressure, power

P*

mass (gravimetric) specific power

Pbat

electric power of the battery

Pt, pt

total pressure

p′

angular velocity about Y‐axis

pe

exit plane static pressure

p∞

atmospheric (ambient) pressure

Q

heat energy per of the system

q

dynamic head, heat energy per unit mass

q′

angular velocity about z‐axis

R

gas constant, reaction

Re

Reynolds number

Recrit

critical Reynolds number

r

radius, angular velocity

r′

angular velocity about the x‐axis

S

area, most of the time, with a subscript identifying the component

SBs

project side area of the fuselage

SH, SHT

horizontal tail reference area

Sn

maximum cross sectional area

SW

wing reference area

SV, SVT

vertical tail reference area

sfc

specific fuel consumption

T

temperature, thrust, time

TC

non dimensional thrust

TF

non dimensional force (for torque)

TSLS

sea level static thrust at takeoff rating

T/W

thrust loading

t/c

thickness to chord ratio

tf

turbofan

Ug

vertical gust velocity

U∞

free stream velocity

u

local velocity along the x‐axis

V

free stream velocity

VA

aircraft stall speed at limit load

VB

aircraft speed at upward gust

VC

aircraft maximum design speed

VD

aircraft maximum dive speed

VS

aircraft stall speed

Ve

exit plane velocity (turbofan)

Vep

primary (hot) exit plane velocity (turbofan)

Ves

secondary (cold) exit plane velocity (turbofan)

W

weight, width, rate of energy usage (per hour).

WA

useful work done on aircraft

WE

mechanical work produced by engine

W/Sw

wing loading

wu

upwash deflected velocity

wd

downwash deflected velocity

x

distance along the x‐axis

y

distance along the y‐axis

z

vertical distance

Greek Symbols

α

angle of attack

αeff

effective angle of incidence

β

CG angle with vertical at main wheel, blade pitch angle, side slip angle

Γ

dihedral angle, circulation

γ

ratio of specific heat, fuselage clearance angle

Δ

increment measure

δ

boundary layer thickness

ε

downwash angle

ηt

thermal efficiency

ηp

propulsive efficiency

ηo

overall efficiency

Λ

wing sweep, subscript indicates the chord line.

λ

taper ratio

μ

friction coefficient, wing mass

ρ

density

θ

elevation angle, flight path angle, fuselage upsweep angle

π

constant = 3.14

σ

atmospheric density ratio

τ

thickness parameter, torque

υ

velocity

ϕ

roll angle, bank angle

ψ

azimuth angle, yaw angle

ω

angular velocity

Subscripts (in many cases the subscripts are spelled out and not listed here)

a

aft

ave

average

ep

primary exit plane

es

secondary exit plane

f

front, fuselage

fb

blockage factor for drag

fh

drag factor for nacelle profile drag (propeller driven)

fus

fuselage

HT

horizontal tail

M

middle

N, nac

nacelle

o

free stream condition

p

primary (hot) flow

s

stall, secondary (cold)...

Produkt-Details

• Erscheint lt. Verlag: 14.12.2018
• Reihe/Serie: Aerospace Series
• Reihe/Serie: Aerospace Series (PEP)
• Reihe/Serie: Aerospace Series (PEP)
• Mitarbeit: Herausgeber (Serie): Peter Belobaba, Jonathan Cooper, Allan Seabridge
• Sprache: englisch
• Themenwelt: Technik ► Bauwesen
• Themenwelt: Technik ► Maschinenbau
• Schlagworte: advanced aircraft design • aerodynamics • Aeronautic & Aerospace Engineering • aeroplane design • Aircraft Aerodynamics • aircraft design concepts • aircraft design performance • aircraft design process • Aircraft Electrical Systems • aircraft engineering • aircraft life cycle costing • aircraft mechanical systems • Aircraft performance • aircraft reliability and safety • aircraft safety design • Aircraft Structural Design • aircraft thermodynamics designing for aircraft nose • airframe design methods • airplane design • Applied Mathematics in Engineering • Bombardier • combat plane design • Conceptual Aircraft Design: An Industrial Approach</p> • design for air combat • guide to aircraft design • Institute of Mechanical Engineers • jet plane design • <p>aircraft design • Luft- u. Raumfahrttechnik • Maschinenbau • Maschinenbau - Entwurf • Mathematics • Mathematik • Mathematik in den Ingenieurwissenschaften • mechanical engineering • Mechanical Engineering - Design • Royal Aeronautical Society • structural design of composite airframes • structural design of metallic airframes • value driven design for aircrafts
• ISBN-10: 1-119-50026-5 / 1119500265
• ISBN-13: 978-1-119-50026-1 / 9781119500261