1st Edition

Aircraft Design Concepts
An Introductory Course

  • Available for pre-order. Item will ship after December 24, 2021
ISBN 9781138033399
December 24, 2021 Forthcoming by CRC Press
590 Pages 462 B/W Illustrations

USD $160.00

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Book Description

Aircraft Design Concepts: An Introductory Course introduces the principles of aircraft design through a quantitative approach developed from the author’s extensive experience in teaching aircraft design. Building on prerequisite courses, the text develops basic design skills and methodologies, while also explaining the underlying physics.

The book uses a historical approach to examine a wide range of aircraft types and their design. Numerous charts, photos, and illustrations are provided for in-depth view of aeronautical engineering. It addresses conventional tail-aft monoplanes, "flying-wing", biplane, and canard configurations. Providing detailed analysis of propeller performance, the book starts with simple blade-element theory and builds to the Weick method.

Written for senior undergraduate and graduate students taking a single-semester course on Aircraft Design or Aircraft Performance, the book imparts both the technical knowledge and creativity needed for aircraft design.

Table of Contents

1.Introduction 1.1 Design Features 1.2 Different Materials in Column Buckling 1.3 Illustrative Examples of Wood, Metal, and Composite Airplanes 1.4 Example Wing Structures 2.Aerodynamic Review 2.1 Airfoils 2.2 Wings 2.3 Bodies 2.4 Undercarriage 2.5 Wing-Body Combination 2.6 Complete-Aircraft Aerodynamics (for a Tail-Aft Monoplane) 2.6.1. Pitching Moment (with non-extended undercarriage) 2.6.2. Pitching Moment (with extended undercarriage) 2.7. Numerical Example 2.7.1. Wing 2.7.2. Tail 2.7.3. Body 2.7.4. Undercarriage 2.7.5. Complete Airplane Lift and Drag Coefficients 2.7.6. Complete Airplane Moment Characteristics 2.8. A Final Comment 3.Propeller Analysis 3.1 Simple Blade-Element Analysis 3.2 Actuator-Disk Momentum Theory 3.3 Extensions to the Simple Blade-Element Analysis 3.4 Method of Calculation. 3.5 Numerical Example 3.6 Propeller Airfoils 3.7 Matlab Program 4.Flying Wings (or Tailless Airplanes) 4.1 “Flying Planks” 4.2 Swept Flying Wings 4.3 Paragliders 4.4 Rogallo-Type Hang Gliders 4.5 Span-Loader Flying Wings 4.6 A Canadian Flying-Wing Glider 4.7 An Approximate Method for Estimating the Aerodynamic Characteristics of Wings with Variable Twist, Taper and Sweep 4.7.1.Example 1, Straight-Tapered Linearly-Twisted Wing. 4.7.2.Example 2, Double-Swept and Double-Tapered Wing 4.7.3.Matlab Computer Program 4.8.“Delta” Tailless Aircraft 4.9.Final Observations 5.Canard Airplanes and Biplanes 5.1 Canard Airplanes 5.1.1. An Approximate Method for Estimating the Aerodynamic 5.1.2. Characteristics of Canard Airplanes 5.1.3. Example, Canard Glider 5.2. Biplanes 5.2.1. An Approximate Method for Estimating the Aerodynamic 5.2.2. Characteristics of Biplanes with Wings of Equal Spans and Areas 5.2.3. Example, “Slow SHARP” Biplane 5.2.4. Further Considerations of Biplane Analysis 5.2.5. Example, Biplane Glider 5.2.6. Final Biplane Comment 6.Flight Dynamics 6.1. Introduction 6.2. Aircraft Longitudinal Small-Perturbation Dynamic Equations 6.2.1 Non-Dimensional Form of the Equations 6.2.2. Estimation of the Longitudinal Stability Derivatives 6.2.3. Longitudinal Numerical Example (“Scholar” Tail-Aft Monoplane) 6.3. Aircraft Lateral Small-Perturbation Dynamic Equations 6.3.1. Non-Dimensional Form of the Equations. 6.3.2. Estimation of the Lateral Stability Derivatives 6.3.3. Example Lateral Stability Derivatives for the “Scholar” Tail- 6.3.4. Aft Monoplane 6.4. Radii-of-Gyration Values for Representative Airplanes 6.5. Definitions of Stability 6.6. Longitudinal Dynamic Stability 6.6.1. Numerical Example 6.6.2. Comments on alpha and theta 6.6.3. Flight Paths 6.6.4. Approximate Equations 6.6.5. Roots-Locus Plots 6.7. Lateral Dynamic Stability 6.7.1. Flight Paths 6.7.2. Approximate Equations 6.7.3. Roots-Locus Plots 6.7.4. Stability-Boundary Plot 6.8. Addendum 7.Performance 7.1. Glide Tests 7.2. Equilibrium Flight 7.3. Trim State 7.4. Full Solution 7.5. Performance Parameters 7.3. Takeoff Run 7.4. Final Comments 8.Balloons and Airships 8.1. Free Balloons 8.2. The Physics of Buoyancy 8.3. Tethered Balloons 8.4. Airships 8.5. Aerodynamics of Finned Axisymmetric Bodies 8.6. A Method for Calculating the Longitudinal Static Aerodynamic Coefficients 8.6.1. Example 1: Small Aerostat 8.6.2. Example 2: Airship ZRS-4 “Akron” 5.98m Wind-Tunnel Model 8.6.3. Example 3: “Wingfoot 2” Airship (Zeppelin LZ N07) 8.6.4. Example 4: TCOM CBV-71 Aerostat 8.7. Aerodynamic Corrections for Inflated Fins 8.6. Additional Observations about Aerostats 8.7. Lateral Force and Yawing Moment Calculation 8.8. Numerical Example 8.9. Airship Aerodynamic Mystery 8.10. Matlab Program. Appendix A: Multhropp Body-Moment Equation Appendix B: Alternative Swept-Wing Analysis Appendix C: Rigid-Body Equations of Motion Appendix D: Apparent-Mass Effects Appendix E: Lift of Finite Wings Due to Oscillatory Plunging Acceleration

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James DeLaurier has worked as an aerospace engineer, consultant, and professor. He received his Ph.D. from Stanford University and has worked at McDonnell Aircraft, the NASA Ames Research Center, the Sheldahl Corporation, and the Battelle Memorial Foundation. Until his retirement in 2006, Dr. DeLaurier was a professor of Aerospace Engineering at the University of Toronto. His specialties include aircraft design, lighter-than-air aerial vehicles, flapping-wing flying machines, and remote-piloted/microwave-powered aircraft.