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.
Author(s): James DeLaurier
Publisher: CRC Press
Year: 2022
Language: English
Pages: 580
City: Boca Raton
Cover
Half Title
Title Page
Copyright Page
Dedication
Contents
Preface
Acknowledgements
Author
Chapter 1: Introduction
Design Features
Different Materials in Column Buckling
Illustrative Examples of Wood, Metal and Composite Airplanes
Examples Wing Structures
Chapter 2: Aerodynamic Review
Airfoils
Wings
Bodies
Undercarriage
Wing-Body Combination
Complete-Aircraft Aerodynamics (for a Tail-Aft Monoplane)
Lift
Drag
Pitching Moment (with non-extended undercarriage)
Pitching Moment (with extended undercarriage)
Numerical Example
Wing
Tail
Body
Propeller
Undercarriage
Complete Airplane Lift and Drag Coefficients
Complete Airplane Moment Characteristics
A Final Comment
Chapter 3: Propeller Analysis
Simple Blade-Element Analysis
Actuator-Disk Momentum Theory
Extensions to the Simple Blade-Element Analysis
Method of Calculation
Numerical Example
Application of the Analysis
Propeller Airfoils
Matlab Program
Chapter 4: Flying Wings (or Tailless Airplanes)
“Flying Planks”
Swept Flying Wings
Paragliders
Rogallo-Type Hang Gliders
Span-Loader Flying Wings
A Canadian Flying-Wing Glider
An Approximate Method for Estimating the Aerodynamic Characteristics of Wings with Variable Twist, Taper and Sweep
Example 1, Straight-Tapered Linear-Twisted Wing
Example 2, Double-Swept and Double-Tapered Wing
Matlab Computer Program
“Delta” Tailless Aircraft
Final Observations
Chapter 5: Canard Airplanes and Biplanes
Canard Airplanes
An Approximate Method for Estimating the Aerodynamic Characteristics of Canard Airplanes
Example, Rectangular Wing
Example, Canard Glider
Biplanes
An Approximate Method for Estimating the Aerodynamic Characteristics of Biplanes with Wings of Equal Spans and Areas
Example, “Slow SHARP” Biplane
Further Considerations of Biplane Analysis
Example, Biplane Glider
Final Biplane Comment
Chapter 6: Flight Dynamics
Introduction
Aircraft Longitudinal Small-Perturbation Dynamic Equations
Non-Dimensional Form of the Equations
Estimation of the Longitudinal Stability Derivatives
The ( )0 Terms
The û Derivatives
The α Derivatives
The ˆq derivatives
The Dû Derivatives
The Dα Derivatives
The Dˆq Derivatives
The Propulsion Derivatives
Longitudinal Numerical Example (“Scholar” Tail-Aft Monoplane)
Example Values of (CX)0, (CZ)0 and (CM)0
Example Values of CXα, CZα and CMα
Example values of CXq, CZq and CMq
Example Values of CXDU and CMDU
Example Values of CZDα and CMDα
Example Values of CXDq, CZDq and CMDq
Example Values of T̂Xu, T̂Xα and T̂Zα.
Aircraft Lateral Small-Perturbation Dynamic Equations
Non-Dimensional Form of the Equations
Estimation of the Lateral Stability Derivatives
The β Derivatives:
The rˆ Derivatives
The pˆ Derivatives:
The Dβ Derivatives:
The Drˆ Derivatives
The Dpˆ Derivatives
Example Lateral Stability Derivatives for the “Scholar” Tail-Aft Monoplane
Example Value of CYβ
An Extension to the Analysis
Example Value of CNβ
Example Value of CL˜ β
Example Value of CYr
Example Value of CNr
Example Value of CL˜ r
Example Value of CYp
Example Value of CNp
Example Value of CL˜ p
Example Value of CYDβ
Example Value of CNDβ
Example Value of CL˜ Dβ
Example Value of CYDr
Example Value of CNDr
An Extension to the Analysis
Example Value of CL˜ Dr
Example Value of CYDp
Example Value of CNDp
Example Value of CL˜ Dp
An Extension to the Analysis
Radii-of-Gyration Values for Representative Airplanes
Definitions of Stability
Longitudinal Dynamic Stability
Numerical Example
Comments on α and θ
Flight Paths
Approximate Equations
Short-Period Mode
Phugoid Mode
Roots-Locus Plots
Lateral Dynamic Stability
Flight Paths
Approximate Equations
Spiral Mode
Rolling Mode
Dutch-Roll Mode
Roots-Locus Plots
Stability-Boundary Plot
Addendum
Chapter 7: Performance
Glide Tests
Equilibrium Flight
Trim State
Full Solution
Performance Parameters
Take-Off Run
Wood’s Methodology
Final Comments
Chapter 8: Balloons and Airships
Free Balloons
The Physics of Buoyancy
Tethered Balloons
Airships
Aerodynamics of Finned Axisymmetric Bodies
A Method for Calculating the Longitudinal Static Aerodynamic Coefficients
Example 1: Small Aerostat
Example 2: Airship ZRS-4 “Akron” 5.98m Wind-Tunnel Model
Example 3: Goodyear “Wingfoot2” Airship (Zeppelin LZ N07)
Example 4: TCOM CBV-71 Aerostat
Summary of Example Parameters
Aerodynamic Corrections for Inflated Fins
Additional Observations about Aerostats
Lateral Force and Yawing Moment Calculation
Airship Aerodynamic Mystery
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
Index
