By N.F. Krasnov
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Additional resources for Aerodynamics: Fundamentals of Theory, Aerodynamics of an Airfoil and Wing; Methods of Aerodynamic Calculation
Flo\y). Idealizatioll of Ihe procpss ('onsists in assuming tho :\Iach number to equal zero within this rpgion of speeds because small disturbancps (SOlllld oscillations) propagatp ill c\]l incompressihle l1llic! at an inlinitely high spope! ane!. conspqupntly, the ratio of the f1ight speec! to that of sOllne! tOllds to zero. Modern craft hayp high airspeeds at which flow O\'PI' them is attended by a considerahle changp in the rrpSSllre and. cOllseql1elltly. by a substantial change in thp densit~, all(1 temperature.
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. If after the stopping of sllch action these angles diminish, tending to their initial values, we have static lateral stability.
The position of a craft relative to this coordinate system is determined by three angles: the yawing (course) angle ~J, the pitching angle &, and the rolling (banking) angle "(. The angle ~ is formed by the projection of the longitudinal body axis Ox onto the horizontal plane x~Oy~ (Ox *) and the axis Ox~; this angle is positive if the axis Ox~ coincides with the projection of Ox* by clockwise rotation about the axis Oy~. The angle & is that between the axis Ox and the horizontal plane x~Oz; and will be positive if this plane is below the longitudinal -------- - - - - - -..