Read e-book online Aerodynamics: Fundamentals of Theory, Aerodynamics of an PDF

By N.F. Krasnov

ISBN-10: 0828531196

ISBN-13: 9780828531191

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Additional resources for Aerodynamics: Fundamentals of Theory, Aerodynamics of an Airfoil and Wing; Methods of Aerodynamic Calculation

Example text

The velocity of the flow is zero at the wall (see Fig. 4) and gradually increases with the distance from the surface. The shear stress changes accordingly-at the wall it is considerably greater than far from it. The thin layer of fluid adjacent to the surface of the body in a flow that is characterized by large velocity gradients along a normal to it and, consequently, by considerable shear stresses is called a boundary layer. In this layer, the viscous forces have a magnitude of the Ch. 1. Basic Information from Aerodynamics 35 same order as all the other forces (for example, the forces of inertia an d pressure) governing motion and, therefore, taken in to account in the equations of motion.

The mean aerodynamic chord is determined as the chord of the airfoil of an equivalent rectangular wing for which with an identical wing plan area the moment aerodynamic characteristics are approximately the same as of the given wing. The length of the mean aerodynamic chord and the coordinate of its leading edge are determined as follows (Fig. 2): 1/2 XAO=_2_ (' Sw j o bxdz When calculating forces and moments according to known aerodynamic coefficients, the geometric dimensions must be used for which these coefficients were evaluated.

I. Theory. Jer Tvrbulent tayer 2 y2 Fig. e. mass, momentum, and energy are transferred by fluid particles of a vortex origin. Hence it follows that fluctuations are characterized by a statistical association. The correlation coefficient between fluctuations at points of the region of a disturbed flow being studied is a quantitative measure of this association. 3) If there is no statistical association between the quantities cp and = 0; if, conversely, these quantities are regularly assoeiated, the correlation coefficient R = 1.

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Aerodynamics: Fundamentals of Theory, Aerodynamics of an Airfoil and Wing; Methods of Aerodynamic Calculation by N.F. Krasnov

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