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
I. Theory. _ Fig. ; x flowl The main part of the boundary layer outside of the viscolls sublayer is called the turbulent core. The studying of the motion in a boundary layer is associated with the simultaneous investigation of the flow of a fluid in a turbulent core and a viscous sublayer. The change in the velocity over the cross section of the boundary layer is characterized by its gradually growing with the distance from the wall and asymptotically approaching the value of the velocity in the external flow.
This indicates a difference in the value of the coefficients of static longitudinal stability. A glance at Fig. 1, for example, shows that upon a certain deflection of the elevator «\) , stability at low angles of attaek (a ~ albal) may change to instability at larger values of them (a ~ a2bal) and may be restored at still larger angles (a ~ aabal). To avoid this phenomenon, it is necessary to limit the range of the angles of attack to low values at which a linear dependence of the pitching moment coefficient on the angle of attack and elevator angle is retained.
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 -------- - - - - - -.. ----. 40 Pt. I. Theory. Aerodynamics of an Airfoil and a Wing body axis. The angle y is formed upon the rotation (rolling) of a craft about the longitudinal axis Ox and is measured in magnitude as the angle between the lateral body axis and the axis OZg displaced to a position corresponding to a zero yawing angle (or as the angle between the axis Oz and its projection onto a horizontal plane-the axis Oz;).