Theory of Wing Sections

Häftad, Engelska, 2000

Del i serien Dover Books on Aeronautical Engineering

254 kr

Skickas . Fri frakt över 249 kr.

Beskrivning

A reference for engineers and students, this volume devotes more than 300 pages to theoretical and experimental considerations. It progresses from elementary materials to methods used in the design of NACA low-drag airfoils, and it presents techniques for using wing-section data to predict wing characteristics. Requires differential and integral calculus and elementary mechanics. 1949 edition.

Produktinformation

Utgivningsdatum:2000-02-01
Mått:145 x 215 x 37 mm
Vikt:720 g
Format:Häftad
Språk:Engelska
Serie:Dover Books on Aeronautical Engineering
Antal sidor:704
Förlag:Dover Publications Inc.
ISBN:9780486605869

Utforska kategorier

Innehållsförteckning

PREFACE TO DOVER EDITIONPREFACE1. THE SIGNIFICANCE OF WING-SECTION CHARACTERISTICSSymbols.The Forces on Wings.Effect of Aspect Ratio.Application of Section Data to Monoplane Wings:a. Basic Concepts of Lifting-line Theory.b. Solutions for Linear Lift Curves.c. Generalized Solution.Applicability of Section Data.2. SIMPLE TWO-DIMENSIONAL FLOWSSymbols.Introduction.Concept of a Perfect Fluid.Equations of Motion.Description of Flow Patterns.Simple Two-dimensional Flows:a. Uniform Stream.b. Sources and Sinks.c. Doublets.d. Circular Cylinder in a Uniform Stream.e. Vortex.f. Circular Cylinder with Circulation.3. THEORY OF WING SECTIONS OF FINITE THICKNESSSymbols.Introduction.Complex Variables.Conformal Transformations.Transformation of a Circle into a Wing Section.Flow about Arbitrary Wing Sections.Empirical Modification of the Theory.Design of Wing Sections.4. THEORY OF THIN WING SECTIONSSymbols.Basic Concepts.Angle of Zero Lift and Pitching Moment.Design of Mean Lines.Engineering Applications of Section Theory.5. THE EFFECTS OF VISCOSITYSymbols.Concept of Reynolds Number and Boundary Layer.Flow around Wing Sections.Characteristics of the Laminar Layer.Laminar Skin Friction.Momentum Relation.Laminar Separation.Turbulent Flow in Pipes.Turburlent Skin Friction.Calculation of Thickness of the Turbulent Layer.Turbulent Separation.Transition from Laminar to Turbulent Flow.Calculation of Profile Drag.Effect of Mach Number on Skin Friction.6. FAMILIES OF WING SECTIONSSymbols.Introduction.Method of Combining Mean Lines and Thickness Distributions.NACA Four-digit Wing Sections:a. Thickness Distributions.b. Mean Lines.c. Numbering System.d. Approximate Theoretical Characteristics.NACA Five-digit Wing Sections:a. Thickness Distributions.b. Mean Lines.c. Numbering System.d. Approximate Theoretical Characteristics.Modified NACA Four-and Five-digit Series Wing Sections.NACA 1-Series Wing Sections:a. Thickness Distributions.b. Mean Lines.c. Numbering System.d. Approximate Theoretical Characteristics.NACA 6-Series Wing Sections: a. Thickness Distributions.b. Mean Lines.c. Numbering System.d. Approximate Theoretical Characteristics.NACA 7-Series Wing Sections.Special Combinations of Thickness and Camber.7. EXPERIMENTAL CHARACTERISTICS OF WING SECTIONS.Symbols.Introduction.Standard Aerodynamic Characteristics.Lift Characteristics:a. Angle of Zero Lift.b. Lift-curve Slope.c. Maximum Lift.d. Effect of Surface Condition on Lift Characteristics.Drag Characteristics:a. Minimum Drag of Smooth Wing Sections.b. Variation of Profile Drag with Lift Coefficient.c. Effect of Surface Irregularities on Drag Characteristics.d. Unconservative Wing Sections.Pitching moment Characteristics.8. HIGH-LIFT DEVICESSymbols.Introduction.Plain Flaps.Split Flaps.Slotted Flaps:a. Description of Slotted Flaps.b. Single-slotted Flaps.c. External-aifoil Flaps.d. Double-slotted Flaps.Leading-edge High-lift Devices:a. Slats.b. Slots.c. Leading-edge Flaps.Boundary-layer Control.The Chordwise Load Distribution over Flapped Wing Sections.9. EFFECTS OF COMPRESSIBILITY AT SUBSONIC SPEEDSSymbols.Introduction.Steady Flow through a Stream Tube:a. Adiabatic Lawb. Velocity of Soundc. Bernoulli's Equation for Compressible Flow.d. Cross-sectional Areas and Pressures in a Stream Tube.e. Relations for a Normal Shock.First-order Compressibility Effects:a. Glauert-Prandtl Ruleb. Effect of Mach Number on the Pressure Coefficient.Flow about Wing Sections at High Speed:a. Flow at Subcritical Mach Numbers.b. Flow at Supercritical Mach Numbers.Experimental Wing Characteristics at High Speeds:a. Lift Characteristics.b. Drag Characteristics.c. Moment Characteristics.Wings for High-speed Applications.REFERENCESAPPENDIX I. Basic Thickness FormsII. Mean LinesIII. Airfoil OrdinatesIV. Aerodynamic Characteristics of Wing SectionsINDEX