x

Our Privacy Policy has changed. By using this site, you agree to the Privacy Policy.

Low-Speed Aerodynamics

ISBN-10: 0521665523
ISBN-13: 9780521665520
Edition: 2nd 2001 (Revised)
Buy it from $108.14
This item qualifies for FREE shipping

*A minimum purchase of $35 is required. Shipping is provided via FedEx SmartPost® and FedEx Express Saver®. Average delivery time is 1 – 5 business days, but is not guaranteed in that timeframe. Also allow 1 - 2 days for processing. Free shipping is eligible only in the continental United States and excludes Hawaii, Alaska and Puerto Rico. FedEx service marks used by permission."Marketplace" orders are not eligible for free or discounted shipping.

30 day, 100% satisfaction guarantee

If an item you ordered from TextbookRush does not meet your expectations due to an error on our part, simply fill out a return request and then return it by mail within 30 days of ordering it for a full refund of item cost.

Learn more about our returns policy

Description: Low-speed aerodynamics is important in the design and operation of aircraft flying at low Mach number, and in ground and marine vehicles. This text offers the theory of incompressible, inviscid, and irrotational aerodynamics.

New Starting from $108.14
what's this?
Rush Rewards U
Members Receive:
coins
coins
You have reached 400 XP and carrot coins. That is the daily max!
You could win $10,000

Get an entry for every item you buy, rent, or sell.

Study Briefs

Limited time offer: Get the first one free! (?)

All the information you need in one place! Each Study Brief is a summary of one specific subject; facts, figures, and explanations to help you learn faster.

Add to cart
Study Briefs
Periodic Table Online content $4.95 $1.99
Add to cart
Study Briefs
Medical Terminology Online content $4.95 $1.99
Add to cart
Study Briefs
Medical Math Online content $4.95 $1.99

Customers also bought

Loading
Loading
Loading
Loading
Loading
Loading
Loading
Loading
Loading
Loading

Book details

Edition: 2nd
Copyright year: 2001
Publisher: Cambridge University Press
Publication date: 2/5/2001
Binding: Paperback
Pages: 630
Size: 7.25" wide x 10.25" long x 1.00" tall
Weight: 2.332
Language: English

Low-speed aerodynamics is important in the design and operation of aircraft flying at low Mach number, and in ground and marine vehicles. This text offers the theory of incompressible, inviscid, and irrotational aerodynamics.

Preface
Preface to the First Edition
Introduction and Background
Description of Fluid Motion
Choice of Coordinate System
Pathlines, Streak Lines, and Streamlines
Forces in a Fluid
Integral Form of the Fluid Dynamic Equations
Differential Form of the Fluid Dynamic Equations
Dimensional Analysis of the Fluid Dynamic Equations
Flow with High Reynolds Number
Similarity of Flows
Fundamentals of Inviscid, Incompressible Flow
Angular Velocity, Vorticity, and Circulation
Rate of Change of Vorticity
Rate of Change of Circulation: Kelvin's Theorem
Irrotational Flow and the Velocity Potential
Boundary and Infinity Conditions
Bernoulli's Equation for the Pressure
Simply and Multiply Connected Regions
Uniqueness of the Solution
Vortex Quantities
Two-Dimensional Vortex
The Biot-Savart Law
The Velocity Induced by a Straight Vortex Segment
The Stream Function
General Solution of the Incompressible, Potential Flow Equations
Statement of the Potential Flow Problem
The General Solution, Based on Green's Identity
Summary: Methodology of Solution
Basic Solution: Point Source
Basic Solution: Point Doublet
Basic Solution: Polynomials
Two-Dimensional Version of the Basic Solutions
Basic Solution: Vortex
Principle of Superposition
Superposition of Sources and Free Stream: Rankine's Oval
Superposition of Doublet and Free Stream: Flow around a Cylinder
Superposition of a Three-Dimensional Doublet and Free Stream: Flow around a Sphere
Some Remarks about the Flow over the Cylinder and the Sphere
Surface Distribution of the Basic Solutions
Small-Disturbance Flow over Three-Dimensional Wings: Formulation of the Problem
Definition of the Problem
The Boundary Condition on the Wing
Separation of the Thickness and the Lifting Problems
Symmetric Wing with Nonzero Thickness at Zero Angle of Attack
Zero-Thickness Cambered Wing at Angle of Attack-Lifting Surfaces
The Aerodynamic Loads
The Vortex Wake
Linearized Theory of Small-Disturbance Compressible Flow
Small-Disturbance Flow over Two-Dimensional Airfoils
Symmetric Airfoil with Nonzero Thickness at Zero Angle of Attack
Zero-Thickness Airfoil at Angle of Attack
Classical Solution of the Lifting Problem
Aerodynamic Forces and Moments on a Thin Airfoil
The Lumped-Vortex Element
Summary and Conclusions from Thin Airfoil Theory
Exact Solutions with Complex Variables
Summary of Complex Variable Theory
The Complex Potential
Simple Examples
Uniform Stream and Singular Solutions
Flow in a Corner
Blasius Formula, Kutta-Joukowski Theorem
Conformal Mapping and the Joukowski Transformation
Flat Plate Airfoil
Leading-Edge Suction
Flow Normal to a Flat Plate
Circular Arc Airfoil
Symmetric Joukowski Airfoil
Airfoil with Finite Trailing-Edge Angle
Summary of Pressure Distributions for Exact Airfoil Solutions
Method of Images
Generalized Kutta-Joukowski Theorem
Perturbation Methods
Thin-Airfoil Problem
Second-Order Solution
Leading-Edge Solution
Matched Asymptotic Expansions
Thin Airfoil between Wind Tunnel Walls
Three-Dimensional Small-Disturbance Solutions
Finite Wing: The Lifting Line Model
Definition of the Problem
The Lifting-Line Model
The Aerodynamic Loads
The Elliptic Lift Distribution
General Spanwise Circulation Distribution
Twisted Elliptic Wing
Conclusions from Lifting-Line Theory
Slender Wing Theory
Definition of the Problem
Solution of the Flow over Slender Pointed Wings
The Method of R. T. Jones
Conclusions from Slender Wing Theory
Slender Body Theory
Axisymmetric Longitudinal Flow Past a Slender Body of Revolution
Transverse Flow Past a Slender Body of Revolution
Pressure and Force Information
Conclusions from Slender Body Theory
Far Field Calculation of Induced Drag
Numerical (Panel) Methods
Basic Formulation
The Boundary Conditions
Physical Considerations
Reduction of the Problem to a Set of Linear Algebraic Equations
Aerodynamic Loads
Preliminary Considerations, Prior to Establishing Numerical Solutions
Steps toward Constructing a Numerical Solution
Example: Solution of Thin Airfoil with the Lumped-Vortex Element
Accounting for Effects of Compressibility and Viscosity
Singularity Elements and Influence Coefficients
Two-Dimensional Point Singularity Elements
Two-Dimensional Point Source
Two-Dimensional Point Doublet
Two-Dimensional Point Vortex
Two-Dimensional Constant-Strength Singularity Elements
Constant-Strength Source Distribution
Constant-Strength Doublet Distribution
Constant-Strength Vortex Distribution
Two-Dimensional Linear-Strength Singularity Elements
Linear Source Distribution
Linear Doublet Distribution
Linear Vortex Distribution
Quadratic Doublet Distribution
Three-Dimensional Constant-Strength Singularity Elements
Quadrilateral Source
Quadrilateral Doublet
Constant Doublet Panel Equivalence to Vortex Ring
Comparison of Near and Far Field Formulas
Constant-Strength Vortex Line Segment
Vortex Ring
Horseshoe Vortex
Three-Dimensional Higher Order Elements
Two-Dimensional Numerical Solutions
Point Singularity Solutions
Discrete Vortex Method
Discrete Source Method
Constant-Strength Singularity Solutions (Using the Neumann B.C.)
Constant Strength Source Method
Constant-Strength Doublet Method
Constant-Strength Vortex Method
Constant-Potential (Dirichlet Boundary Condition) Methods
Combined Source and Doublet Method
Constant-Strength Doublet Method
Linearly Varying Singularity Strength Methods (Using the Neumann B.C.)
Linear-Strength Source Method
Linear-Strength Vortex Method
Linearly Varying Singularity Strength Methods (Using the Dirichlet B.C.)
Linear Source/Doublet Method
Linear Doublet Method
Methods Based on Quadratic Doublet Distribution (Using the Dirichlet B.C.)
Linear Source/Quadratic Doublet Method
Quadratic Doublet Method
Some Conclusions about Panel Methods
Three-Dimensional Numerical Solutions
Lifting-Line Solution by Horseshoe Elements
Modeling of Symmetry and Reflections from Solid Boundaries
Lifting-Surface Solution by Vortex Ring Elements
Introduction to Panel Codes: A Brief History
First-Order Potential-Based Panel Methods
Higher Order Panel Methods
Sample Solutions with Panel Codes
Unsteady Incompressible Potential Flow
Formulation of the Problem and Choice of Coordinates
Method of Solution
Additional Physical Considerations
Computation of Pressures
Examples for the Unsteady Boundary Condition
Summary of Solution Methodology
Sudden Acceleration of a Flat Plate
The Added Mass
Unsteady Motion of a Two-Dimensional Thin Airfoil
Kinematics
Wake Model
Solution by the Time-Stepping Method
Fluid Dynamic Loads
Unsteady Motion of a Slender Wing
Kinematics
Solution of the Flow over the Unsteady Slender Wing
Algorithm for Unsteady Airfoil Using the Lumped-Vortex Element
Some Remarks about the Unsteady Kutta Condition
Unsteady Lifting-Surface Solution by Vortex Ring Elements
Unsteady Panel Methods
The Laminar Boundary Layer
The Concept of the Boundary Layer
Boundary Layer on a Curved Surface
Similar Solutions to the Boundary Layer Equations
The von Karman Integral Momentum Equation
Solutions Using the von Karman Integral Equation
Approximate Polynomial Solution
The Correlation Method of Thwaites
Weak Interactions, the Goldstein Singularity, and Wakes
Two-Equation Integral Boundary Layer Method
Viscous-Inviscid Interaction Method
Concluding Example: The Flow over a Symmetric Airfoil
Enhancement of the Potential Flow Model
Wake Rollup
Coupling between Potential Flow and Boundary Layer Solvers
The Laminar/Turbulent Boundary Layer and Transition
Viscous-Inviscid Coupling, Including Turbulent Boundary Layer
Influence of Viscous Flow Effects on Airfoil Design
Low Drag Considerations
High Lift Considerations
Flow over Wings at High Angles of Attack
Flow Separation on Wings with Unswept Leading Edge - Experimental Observations
Flow Separation on Wings with Unswept Leading Edge - Modeling
Flow Separation on Wings with Highly Swept Leading Edge - Experimental Observations
Modeling of Highly Swept Leading-Edge Separation
Possible Additional Features of Panel Codes
Airfoil Integrals
Singularity Distribution Integrals
Principal Value of the Lifting Surface Integral I[subscript L]

×
Free shipping on orders over $35*

*A minimum purchase of $35 is required. Shipping is provided via FedEx SmartPost® and FedEx Express Saver®. Average delivery time is 1 – 5 business days, but is not guaranteed in that timeframe. Also allow 1 - 2 days for processing. Free shipping is eligible only in the continental United States and excludes Hawaii, Alaska and Puerto Rico. FedEx service marks used by permission."Marketplace" orders are not eligible for free or discounted shipping.

Learn more about the TextbookRush Marketplace.

×