By Hermann T. Schlichting, Erich A. Truckenbrodt (transl. by Heinrich J. Ramm)
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Extra info for Aerodynamics of the Airplane
The position of the line of application of the resultant R, for example, on the wing, can be defined as the intersection of the line of application with the profile chord (Fig. 1-7a). This point is called the center of pressure or aerodynamic center of the wing. AZ For small angles of attack, the normal force with the negative sign is, in first approximation, equal to the lift: Z= -L and by introducing the nondimensional coefficients, xL CM Cµ CZ ( 1 -27 a) CM _ dcM CMO CL dCL CL Figure 1-7 Demonstration of location of ( 1 -27b ) aerodynamic center (center of pressure).
Physically, the process described is obviously identical to a sound source at rest in a fluid approaching from the right with velocity w. We have to keep in mind, therefore, the following characteristic difference: When the fluid velocity is smaller than the speed of sound (w a, supersonic flow), pressure disturbances can propagate only within the Mach cone situated downstream of the sound source (Fig.
Introducing the dimensionless coefficients according to Eq. (1-21), the stability coefficients of sideslip acmz acMx and aS? asp are obtained. Q is the dimensionless angular velocity cw,. It is obtained from wX, the half-span s, and the flight velocity V: 5Q,; = E. -I, (1-30) V The rotary motion of an airplane about the vertical axis (yaw) produces additional longitudinal air velocities on the wing that have reversed signs on the two wing halves and that result in an asymmetric normal and tangential force distribution along the wing span, which in turn produces a rolling and a yawing moment.
Aerodynamics of the Airplane by Hermann T. Schlichting, Erich A. Truckenbrodt (transl. by Heinrich J. Ramm)