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
2) Accordingly, the longitudinal stability is determined by the mutual arrangement of the aerodynamic centre and centre of mass of a craft. When the aerodynamic centre is behind the centre of mass (the difference Fa. - XcM is positive)~ the relevant craft is statically stable, and when it is in front of the centre of mass (the difference F a - :reM is negative), the craft is unstable. By correspondingly choosing the centre of mass (or by centering), we can ensure the required margin of static stability.
2. Ch. 1. 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.
When the two centres coincide (xF = XCM), the craft is neutral as regards tl static directional stability (m~z = 0). A particular case of motion of a craft in the plane of the angle of attack can be characterized by a constant angular velocity (Q y = = const) and stabilization with respect to rolling with the aid of an automatic pilot (Q x ;:::::; 0). e. + + + my = myo mg~ m~rl') r m;y Q y = 0 All craft customarily have longitudinal symmetry, therefore myo = O. bal corresponding to the given values of the balance sideslip angle Bba) and the angular velocity Qy.
Aerodynamics: Fundamentals of Theory, Aerodynamics of an Airfoil and Wing; Methods of Aerodynamic Calculation by N.F. Krasnov