Basic Aerodynamics: Incompressible Flow by Gary A. Flandro, Howard M. McMahon, Robert L. Roach PDF

By Gary A. Flandro, Howard M. McMahon, Robert L. Roach

ISBN-10: 0521805821

ISBN-13: 9780521805827

Within the quickly advancing box of flight aerodynamics, it's important for college kids to fully grasp the basics. this article, written by means of popular specialists, basically provides the elemental innovations of underlying aerodynamic prediction method. those recommendations are heavily associated with actual rules so they can be extra effectively retained and their limits of applicability are totally favored. the last word target is to supply the coed with the required instruments to with a bit of luck procedure and resolve of sensible flight automobile layout difficulties of present and destiny curiosity. The textual content is designed to be used in direction in aerodynamics on the complex undergraduate or graduate point. A entire set of workout difficulties is integrated on the finish of every bankruptcy.

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Additional info for Basic Aerodynamics: Incompressible Flow

Example text

The independent parameters are the diameter, d; speed, V; and angular velocity, w; as well as density and viscosity. Determine suitable dimensionless parameters and express the functional dependence among them. Consider the water flow around a circular cylinder of diameter, D, and length, L. In addition to geometry, the drag force is known to depend on liquid speed, V; density, ρ; and viscosity, µ. Express the drag force in dimensionless form as a function of all relevant variables. The static-pressure distribution on a cylinder measured in a laboratory can be expressed in terms of the dimensionless pressure coefficient: Cp = p p∞ .

It must be understood that aerodynamic coefficients also are dependent on geometry. The situation would be simplified if the coefficients were thought of as constants. Then, it would be necessary to compute or measure them only once for a given shape to provide design information for using that shape in a practical application. However, our analysis shows that they vary with special parameters—in this case, the Reynolds and the Mach numbers. To use Eqs. 23, for example, in a wing-design problem, we must have values for all three factors.

Other choices can be made. For instance, in describing the drag of bodies of revolution, we often use the projected frontal area of the body as the reference area, S. Notice that, by using a combination of physical and dimensional reasoning, we now have reduced the aerodynamic-force problem to a convenient and practical form, which can be applied readily in airplane design, for instance. Consider the application of Eq. 22 for determining, for example, the lift on an airplane wing. Three main elements are involved.

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Basic Aerodynamics: Incompressible Flow by Gary A. Flandro, Howard M. McMahon, Robert L. Roach


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