By N.F. Krasnov
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Extra info for Aerodynamics: Fundamentals of Theory, Aerodynamics of an Airfoil and Wing; Methods of Aerodynamic Calculation
The relevant quantities are known as the aerodynamic lift coefficient and the aerodynamic side-force coefficient. 4) for the forces. Let us consider as an example 'such a relation for the pitching moment JVf z ". It is evident that the elementary value of this moment d}1f z a is determined by the sum of the moments about the axis Za of the forces acting on an area dS in a plane at right angles to the axis Za' If the coordinates of the area dS are Ya and X a , the elementary value of the moment is /\.
3) For conditions of a high static stability, we have m~zQz ~ m~abal; consequently 6e . 4) The normal (lift) force coefficient corresponds to the balance angle of attack and elevator angle, namely, c Y. 5) Ch. 1. Basic Information from Aerodynamics 57 The values of c yo are usually very small even for asymmetric configurations (at low 6e and a) and equal zero exactly for craft with axial symmetry. 6 » Static Lateral Stability To analyse the lateral stability of a craft, one must consider jointly the nature of the change in the rolling and sideslip angles upon thesimultaneous action of the perturbing rolling j1:y and yawing Mit moments.
F is the hiction drag. Accordingly, the overall coefficient of drag equals the sum of the coefficients of • pressure and friction drags: Cx a = C x a,p Cx a,1 Similarly, the aerodynamic lift- and side-force coefficients, and also the moments, can be represented as the sum of two components. The forces, moments, and their coefficients are written in the same way in a body axes. For example, the longitudinal-force coeffIcient C x = cx,p cx,f' where cx,p and Xx,r are the coefficients of the longitudinal forces due to pressure and friction, respectively.
Aerodynamics: Fundamentals of Theory, Aerodynamics of an Airfoil and Wing; Methods of Aerodynamic Calculation by N.F. Krasnov
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