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- Category: Aerodynamics for Engineering Students (continued)
- Growth along a flat surface
- Laminar and turbulent flows
- Boundary-layer thickness
- Further thought about the thickening process will make it evident that the increase in velocity that takes place along a normal to the surface must be continuous. Let у be the perpendicular distance from the surface at any point and let и be the corresponding velocity parallel to the surface. If и were to increase discontinuously with у at any point, then at that point du/dy would be infinite. This would imply an infinite shearing stress [since the shear stress r = fi(du/dy)] which is obviously untenable
- The development of the boundary layer
- Viscous flow and boundary layers[35]
- Computational methods
- Wings of finite span
- Other aspects of supersonic wings
- Double wedge aerofoil section
- Aerofoil section made up of unequal circular arcs
- Symmetrical double wedge aerofoil in supersonic flow
- . Supersonic linearized theory (Ackeret's rule)
- Application to swept wings
- Constant chordwise ordinates
- The equations of motion of a compressible fluid
- Subcritical flow, small perturbation theory (Prandtl-Glauert rule)
- Wings in compressible flow
- Two-dimensional supersonic flow past a wedge
- The shock polar
- Plane oblique shock relations
- Shock waves
- Mach wave interference
- Mach wave reflection
- Mach waves
- Mach waves and shock waves in two-dimensional flow
- Pitot tube equation
- Total pressure change across the normal shock
- Velocity change across the normal shock
- Mach number change across the normal shock
- Entropy change across the normal shock
- Temperature rise across the normal shock
- Density jump across the normal shock
- . Taking 7 = 1.4 for air, these equations become
- Pressure-density relations across the shock
- One-dimensional properties of normal shock waves
- One-dimensional flow: plane normal shock waves
- The speed of sound (acoustic speed)
- One-dimensional flow: weak waves
- Variation of mass flow with pressure
- The ratio of areas at different sections of the stream tube in isentropic flow
- Pressure, density and temperature ratios along a streamline in isentropic flow
- Isentropic one-dimensional flow
- Compressible flow
- Computational (panel) methods for wings
- Wings of small aspect ratio
- Swept wings of finite span
- Swept and delta wings
- Load distribution for minimum drag
- General solution of Prandtl's integral equation
- The general theory for wings of high aspect ratio
- Determination of the load distribution on a given wing
- Minimum induced drag condition
- Aerodynamic characteristics for symmetrical general loading
- The general (series) distribution of lift
- The characteristics of a simple symmetric loading - elliptic distribution
- The consequences of downwash - trailing vortex drag
- Relationship between spanwlse loading and trailing vorticity
- The use of vortex sheets to model the lifting effects of a wing
- Vortex sheets
- Ground effects
- Influence of the downwash on the tailplane
- Formation flying effects
- The simplified horseshoe vortex
- Variation of velocity in vortex flow
- Special cases of the BiotSavart law
- The Biot-Savart law
- Helmholtz's theorems
- Laws of vortex motion
- The horseshoe vortex
- The bound vortex system
- The trailing vortex system
- The vortex system
- Finite wing theory
- Computational (panel) methods for two-dimensional lifting flows
- The thickness problem for thin aerofoils
- Thickness problem for thin-aerofoil theory
- The NACA four-digit wing sections
- Particular camber lines
- The normal force and pitching moment derivatives due to pitching[17]
- The jet flap
- The hinge moment coefficient
- The flapped aerofoil
- The general thin aerofoil section
- The thin symmetrical flat plate aerofoil
- The solution of the general equation
- The general thin aerofoil theory
- The development of aerofoil theory
- Circulation and lift (Kutta-Zhukovsky theorem)
- Circulation and vorticity
- The Kutta condition
- Two-dimensional wing theory
- A computational routine in FORTRAN 77
- Computational (panel) methods
- Flow around slender bodies
- The point doublet and the potential flow around a sphere
- Point source and sink in a uniform axisymmetric flow
- Axisymmetric flow from a point source (or towards a point sink)
- . For analysing certain two-dimensional flows, for example the flow over a circular cylinder with and without circulation, it is convenient to work with polar coordinates. The axisymmetric equivalents of polar coordinates are spherical coordinates, for example those used for analysing the flow around spheres. Spherical coordinates are illustrated in Fig. 3.28. In this case none of the coordinate surfaces are plane and the directions of all three velocity components vary over the flow field, depending on the values of the angular coordinates в and ip. In this case the relationships between the velocity components and potential are given by
- Axisymmetric flows (inviscid and incompressible flows)