By Hermann T. Schlichting, Erich A. Truckenbrodt (transl. by Heinrich J. Ramm)
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Additional resources for Aerodynamics of the Airplane
Applying the method of complex functions, von Mises  presents integral formulas for the computation of the force and moment resultants on wing profiles in frictionless flow. They are based on the work of Blasius [71 J. 2-3-2 Inclined Flat Plate The simplest case of a lifting-airfoil profile is the inclined flat plate. The angle between the direction of the incident flow and the direction of the plate is called angle of attack a of the plate. The flow about the inclined flat plate is obtained as shown in Fig.
Sin a. At the plate leading edge, t = -c/2, the velocity is infinitely high. The flow around the plate comes from below, as seen from Fig. 2-8e. On the plate trailing edge, t = +c/2, the tangential velocity has the value u = v cos a. At an arbitrary station of the plate, the tangential velocities on the lower and upper surfaces have a difference in magnitude zi u = uu - ul. At the trailing edge, v u = 0 (smooth flow-off). The nondimensional pressure difference between the lower and upper surfaces, related to the dynamic pressure of the incident flow qr, = (o/2)w',, is [see Eq.
This becomes obvious when the airplane is taken as the source of a disturbance that moves through still air at a velocity V= w. Relative to this moving center of disturbance, pressure waves emanate with the speed of sound a. 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.