Theory and Practice of Aircraft Performance

Textbook introducing the fundamentals of aircraft performance using industry standards and examples: bridging the gap between academia and industry

• Provides an extensive and detailed treatment of all segments of mission profile and overall aircraft performance

• Considers operating costs, safety, environmental and related systems issues

• Includes worked examples relating to current aircraft (Learjet 45, Tucano Turboprop Trainer, Advanced Jet Trainer and Airbus A320 types of aircraft)

• Suitable as a textbook for aircraft performance courses

Auteur

Ajoy Kumar Kundu graduated with Mechanical Engineering degree from Jadavpur University, India, followed by studying in the United Kingdom (Cranfield University and Queen's University Belfast) and in the United States of America (University of Michigan and Stanford University). His professional experience spans more than thirty years in the aircraft industries and nearly 20 years in academia. In India, he was Professor at the Indian Institute of Technology, Kharagpur; and the Chief Designer at the Hindustan Aeronautics, Bangalore. In North America, he served as Research Engineer for the Boeing Aircraft Company, Renton and as Intermediate Engineer for Canadair Ltd. His aeronautical engineering career began in the United Kingdom with Short Brothers and Harland Ltd., retiring from Bombardier Aerospace-Belfast, as Assistant Chief Aerodynamicist. He is currently associated with Queen's University Belfast. He has authored the book title Aircraft Design published by Cambridge University Press. He held British, Canadian and Indian Private Pilot's License. He is a Fellow of the Royal Aeronautical Society and the Institute of Mechanical Engineers, UK.

Professor Mark Price is the Pro-Vice-Chancellor for the Faculty of Engineering and Physical Sciences at Queen's University Belfast. Formerly he was the Head of School of Mechanical and Aerospace Engineering having progressed through his academic career as a Professor of Aeronautics teaching aircraft structures and design, and leading a research team in design and manufacturing. He graduated in 1987 with a 1st Class Honours degree in Aeronautical Engineering from Queen's University Belfast before taking up a post as a stress engineer in Bombardier Aerospace. He returned later to QUB to undertake a PhD in Mechanical Engineering after which he joined TranscenData Europe as a software engineer and project manager to implement his research in their product CADFix. In 1998 he returned to QUB lecturing in aircraft structures and design. With a strong focus on design applications and integrated performance and cost models, including manufacturing processing effects in design simulations, he received the 2006 Thomas Hawksley medal from the IMechE. He has published over 200 articles and supervised 20 PhDs to completion. Mark is a Fellow of the Royal Aeronautical Society and the Institute of Mechanical Engineers, UK.

David Riordan commenced employment with Short Brothers PLC in 1978 as an Undergraduate Apprentice. He then graduated in 1982 from Queen's University Belfast, with a 1st Class Honours degree in Mechanical Engineering. In 1986 he attained an MSc in Advanced Manufacturing Technology from the Cranfield Institute of Technology, England.
David was appointed Chief Technical Engineer during 2002; in which position provides leadership at the Bombardier Belfast site for all activities associated with the technical engineering fields of aerodynamics, thermodynamics, fire safety and noise; mechanical systems, electrical systems, reliability & safety. David is also functionally responsible for the department of Airworthiness and Engineering Quality.
Responsibilities cover all products associated with Bombardier at Belfast, including metallic fuselage barrels (business jet and regional aircraft applications); composite aerostructures (including the composite wing for the Bombardier CSeries aircraft) and engine nacelles (including the complete nacelle system for the PW1400G-JM propulsion system powering the IRKUT MC-21 aircraft).

Contenu

Preface xix

Series Preface xxi

Road Map of the Book xxiii

Acknowledgements xxvii

Nomenclature xxxi

Introduction 1

1.1 Overview 1

1.2 Brief Historical Background 1

1.2.1 Flight in Mythology 1

1.2.2 Fifteenth to Nineteenth Centuries 1

1.2.3 From 1900 to World War I (1914) 3

1.2.4 World War I (19141918) 4

1.2.5 The InterWar Period: the Golden Age (19181939) 7

1.2.6 World War II (19391945) 7

1.2.7 Post World War II 8

1.3 Current Aircraft Design Status 8

1.3.1 Current Civil Aircraft Trends 9

1.3.2 Current Military Aircraft Trends 10

1.4 Future Trends 11

1.4.1 Trends in Civil Aircraft 11

1.4.2 Trends in Military Aircraft 13

1.4.3 Forces and Drivers 14

1.5 Airworthiness Requirements 14

1.6 Current Aircraft Performance Analyses Levels 16

1.7 Market Survey 17

1.8 Typical Design Process 19

1.8.1 Four Phases of Aircraft Design 19

1.9 Classroom Learning Process 23

1.10 Cost Implications 25

1.11 Units and Dimensions 26

1.12 Use of Semiempirical Relations and Graphs 26

1.13 How Do Aircraft Fly? 26

1.13.1 Classification of Flight Mechanics 27

1.14 Anatomy of Aircraft 27

1.14.1 Comparison between Civil and Military Design Requirements 30

1.15 Aircraft Motion and Forces 30

1.15.1 Motion Kinematics 31

1.15.2 Forces Kinetics 33

1.15.3 Aerodynamic Parameters Lift, Drag and Pitching Moment 34

1.15.4 Basic Controls Sign Convention 34

References 36

2 Aerodynamic and Aircraft Design Considerations 37

2.1 Overview 37

2.2 Introduction 37

2.3 Atmosphere 39

2.3.1 Hydrostatic Equations and Standard Atmosphere 39

2.3.2 Nonstandard/Offstandard Atmosphere 47

2.3.3 Altitude Definitions Density Altitude (Offstandard) 48

2.3.4 Humidity Effects 50

2.3.5 Greenhouse Gases Effect 50

2.4 Airflow Behaviour: Laminar and Turbulent 51

2.4.1 Flow Past an Aerofoil 55

2.5 Aerofoil 56

2.5.1 Subsonic Aerofoil 57

2.5.2 Supersonic Aerofoil 64

2.6 Generation of Lift 64

2.6.1 Centre of Pressure and Aerodynamic Centre 66

2.6.2 Relation between Centre of Pressure and Aerodynamic Centre 68

2.7 Types of Stall 71

2.7.1 Buffet 71

2.8 Comparison of Three NACA Aerofoils 72

2.9 HighLift Devices 73

2.10 Transonic Effects Area Rule 74

2.10.1 Compressibility Correction 75

2.11 Wing Aerodynamics 76

2.11.1 Induced Drag and Total Aircraft Drag 79

2.12 Aspect Ratio Correction of 2DAerofoil Characteristics for 3DFinite Wing 79

2.13 Wing Definitions 81

2.13.1 Planform Area, S W 81

2.13.2 Wing Aspect Ratio 82

2.13.3 WingSweep Angle 82

2.13.4 Wing Root (c root) and Tip (c tip) Chords 82

2.13.5 WingTaper Ratio, 82

2.13.6 Wing Twist 82

2.13.7 High/Low Wing 83

2.13.8 Dihedral/Anhedral Angles 83

2.14 Mean Aerodynamic Chord 84

2.15 Compressibility Effect: Wing Sweep 86

2.16 WingStall Pattern and Wing Twist 87

2.17 Influence of Wing Area and Span on Aerodynamics 88

2.17.1 The SquareCube Law 88

2.17.2 Aircraft Wetted Area (A W) versus Wing Planform Area (S W)89 2.17.3 Additional Wing Surface Vortex Lift Strake/Canard 90

2.17.4 Additional Surfaces on Wing Flaps/Slats and HighLift Devices 91

2.17.5 Other Additional Surfaces on Wing 91

2.18 Empennage 92

2.18.1 Tailarm 95

2.18.2 Horizontal Tail (HTail) 95

2.18.3 Vertical Tail (VTail) 96

2.18.4 TailVolume Coefficients 96

2.19 Fuselage 98 2.19.1 Fuselage Axis/ZeroReference Plan...