By N.F. Krasnov
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Additional info for Aerodynamics: Fundamentals of Theory, Aerodynamics of an Airfoil and Wing; Methods of Aerodynamic Calculation
Theory. 0 I\. 4 \ Fig. 17) where n1Z0 is the coeffieient of the moment about a point on the leading edge at c y = 0 (Fig. 6). 17) determines the increment of the moment associated with a change in the normal-force coefficient. If we choose the point Fa on a chord whose coordinate Xn = XF tl is determined by the condition (see Fig. 18) the coefficient of the moment about this point will not depend on and at all (small) angles of attack it will be a constant quantity. This pcint is Cil1led the aerodynamic centre (AC) of the given body.
If after the stopping of sllch action these angles diminish, tending to their initial values, we have static lateral stability. Hence, when investigating lateral stability, one mnst consider simultaneously the change in the aerodynamic coefficients mx and my. In most prac tical cases. however, lateral stahili ty can be eli vided into two simpler kinds-rolling stability and directional stabilityand can be studied separately by considering the change in the relevant moment coeffIcients m\. (1') and my (~).
Basic I nformafion from Aerodynamics 55 The criterion 1" = ~M - cp determines the margin of static stability. It may be negative (static stability), positive (static instability), and zero (neutrality relative to longitudinal stability). The quantity Y is determined by the formula 1" = mzlc y in which the pitching moment coefficient is evaluated about the centre of mass. For small values of ex, the coefficients m z and c y can be written in the form m z = mr;ex, and c y = c~ex. 1) Hence it follow:- that the derivative omzlOc y = m~y may be considered as a criterion determining the qualitative and quantitative characteristics of longitudinal stability.