By Hermann T. Schlichting, Erich A. Truckenbrodt (transl. by Heinrich J. Ramm)
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Additional info for Aerodynamics of the Airplane
A closer investigation of this process shows the importance of the speed of sound-especially the ratio of flight velocity to sonic speed, that is, the Mach number from Eq. (1-16). In terms of fluid mechanics, the airplane can be considered as a sound source. Figure 1-9a shows the propagation of sound waves from a sound source at rest on concentric spherical surfaces. In Fig. 1-9b the sound waves, emitted at equal time intervals, can be seen for a source that moves with one-half the speed of sound, w = a/2.
C (Fig. 2-1b) is another important quantity. From these designated quantities the following six geometric profile parameters may be formed: t/c hlc xtlc xh /c rN/c 2r relative thickness (thickness ratio)* relative camber (camber ratio)* relative thickness position relative camber position relative nose radius trailing edge angle For the complete description of a profile, the profile coordinates of the upper and lower surfaces, zu(x) and zl(x), must also be known. A profile can be considered as originating from a mean camber line z(s)(x) on which is superimposed a thickness distribution (profile teardrop shape) z(t)(x) > 0.
The derivatives for 0 = 0, (8C Y) 0= ap o aCMZI as Q=0 are called stability coefficients of sideslip; in particular, acMZ/aa is called directional stability. All three of these coefficients are strongly dependent on the wing sweepback, besides other influences. Forces and moments in rotary motion An airplane in rotary motion about the axes x, y, z, as specified by the modes of motion of Sec. 1-3-3, is subject to additional velocity components that are produced, for example, locally on the wing and that change linearly with distance from the axis of rotation.
Aerodynamics of the Airplane by Hermann T. Schlichting, Erich A. Truckenbrodt (transl. by Heinrich J. Ramm)