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Posts
- Category: Fundamentals of Aerodynamics (continued)
- Aerodynamic Forces and Moments
- Center of Pressure
- Dimensional Analysis: The Buckingham Pi Theorem
- Flow Similarity
- Fluid Statics: Buoyancy Force
- Types of Flow
- Inviscid Versus Viscous Flow
- Incompressible Versus Compressible Flows
- Mach Number Regimes
- Applied Aerodynamics: The Aerodynamic Coefficients—Their Magnitudes and Variations
- Historical Note: The Illusive Center of Pressure
- Historical Note: Aerodynamic Coefficients
- Summary
- Aerodynamics: Some Fundamental. Principles and Equations
- Review of Vector Relations
- Typical Orthogonal Coordinate Systems
- Line Integrals
- Surface Integrals
- Volume Integrals
- Models of the Fluid: Control Volumes and Fluid Elements
- Finite Control Volume Approach
- Molecular Approach
- Specification of the Flow Field
- Continuity Equation
- Physical principle Mass can be neither created nor destroyed
- Momentum Equation
- An Application of the Momentum Equation: Drag of a Two-Dimensional Body
- Comment
- Energy Equation
- Physical principle Energy can be neither created nor destroyed; it can only change in form
- Interim Summary
- Substantial Derivative
- Fundamental Equations in Terms of the Substantial Derivative
- Pathlines, Streamlines, and Streaklines
- Angular Velocity, Vorticity, and Strain
- Circulation
- Stream Function
- Velocity Potential
- Relationship Between the Stream Function and Velocity Potential
- How Do We Solve the Equations?
- Theoretical (Analytical) Solutions
- Numerical Solutions—Computational Fluid Dynamics (CFD)
- The Bigger Picture
- Fundamentals of Inviscid,. Incompressible Flow
- Bernoulli’s Equation
- Incompressible Flow in a Duct: the Venturi and Low-Speed Wind Tunnel
- Pitot Tube: Measurement of Airspeed
- Pressure Coefficient
- Condition on Velocity for Incompressible Flow
- Governing Equation for Irrotational, Incompressible Flow: Laplace’s Equation
- Infinity Boundary Conditions
- Wall Boundary Conditions
- Uniform Flow: Our First Elementary Flow
- Source Flow: Our Second Elementary Flow
- Combination of a Uniform Flow with a Source and Sink
- Doublet Flow: Our Third Elementary Flow
- Nonlifting Flow Over a Circular Cylinder
- Vortex Flow: Our Fourth Elementary Flow
- Lifting Flow Over a Cylinder
- The Kutta-Joukowski Theorem and the Generation of Lift
- Nonlifting Flows over Arbitrary Bodies: The Numerical Source Panel Method
- Applied Aerodynamics: the Flow over a Circular Cylinder—the Real Case
- Euler—The Origins of Theoretical Fluid Dynamics
- Historical Note: d’Alembert and His Paradox
- Incompressible Flow over Airfoils
- Airfoil Nomenclature
- Airfoil Characteristics
- The Vortex Sheet
- The Kutta Condition
- Without Friction Could We Have Lift?
- Kelvin’s Circulation Theorem and the Starting Vortex
- Classical Thin Airfoil Theory: The Symmetric Airfoil
- The Cambered Airfoil
- The Aerodynamic Center: Additional Considerations
- Design Box The result of Example 4.3 shows that the aerodynamic center for the NACA 23012 airfoil is located ahead of, but very close to, the quarter-chord point. For some other families of airfoils, the aerodynamic center is located behind, but similarly close to, the quarter-chord point. For a given airfoil family, the location of the aerodynamic center depends on the airfoil thickness, as shown in Figure 4.25. The variation of xac with thickness for the NACA 230XX family is given in Figure 4.25a. Here, the aerodynamic center is ahead of the quarter-chord point, and becomes progressively farther ahead as the airfoil thickness is increased. In contrast, the variation of iac with thickness for the NACA 64-2XX family is given in Figure 4.25b. Here, the aerodynamic center is behind the quarter-chord point, and becomes progressively farther behind as the airfoil thickness is increased. From the point of view of purely aerodynamics, the existence of the aerodynamic center is interesting, but the specification of the force and moment system on the airfoil by placing the lift and drag at the aerodynamic center and giving the value of M'c as illustrated in Figure 4.23, is not more useful than placing the lift and drag at any other point on the airfoil and giving the value of M' at that point, such as shown in Figure 1.19. However, in flight 0 4 8 12 16 20 24 Airfoil thickness, percent of chord (a) NACA 230XX Airfoil 0 4 8 12 16 20 24 Airfoil thickness, percent of chord (b) NACA 64-2XX Airfoil Figure 4.35 Variation of the location of the aerodynamic center with airfoil thickness, (a) NACA 230XX airfoil, (b) NACA 64-2XX airfoil. (continued)  
- . Lifting Flows over Arbitrary Bodies: The Vortex Panel Numerical Method
- Modern Low-Speed Airfoils
- Applied Aerodynamics: The Flow over an Airfoil—The Real Case
- Historical Note: Early Airplane Design and the Role of Airfoil Thickness
- Historical Note: Kutta, Joukowski, and the Circulation Theory of Lift
- Incompressible Flow. over Finite Wings
- The Vortex Filament, the Biot-Savart Law, and Helmholtz’s Theorems
- Prandtl’s Classical Lifting-Line Theory
- General Lift Distribution
- Effect of Aspect Ratio
- Physical Significance
- A Numerical Nonlinear Lifting-Line Method
- The Lifting-Surface Theory and the Vortex Lattice Numerical Method
- . Applied Aerodynamics: The Delta Wing
- Prandtl—The Early Development of Finite-Wing Theory
- Historical Note: Prandtl—The Man
- Three-Dimensional. Incompressible Flow
- Three-Dimensional Source
- Three-Dimensional Doublet
- Flow Over A Sphere
- General Three-Dimensional Flows: Panel Techniques
- Applied Aerodynamics: The Flow Over a Sphere—The Real Case
- Compressible Flow: Some Preliminary Aspects
- A Brief Review of Thermodynamics
- Internal Energy and Enthalpy