Aircraft Design Concepts: An Introductory Course

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. 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