By Hermann T. Schlichting, Erich A. Truckenbrodt (transl. by Heinrich J. Ramm)
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Extra resources for Aerodynamics of the Airplane
2-15), is of practical value for the calculation of lift. However, it must be clarified as to what way the circulation is related to the geometry of the wing profile, to the velocity of the incident flow, and to the angle of attack. This interrelation cannot be determined uniquely from theoretical considerations, so it is necessary to look for empirical results. The technically most important wing profiles have, in general, a more or less sharp trailing edge. Then the magnitude of the circulation can be derived from experience, namely, that there is no flow around the trailing edge, but that the fluid flows off the trailing edge smoothly.
At nonsteady longitudinal motion, new aerodynamic force coefficients must be used, for example, the derivatives aCL ac and aCM a« Angle of attack Figure 1-8 Schematic presentation of quasi-stationary and nonsteady aerodynamic forces. INTRODUCTION 21 W=O w-i a w w=a Figure 1-9 Propagation of sound waves from a sound source moving at the velocity w through a fluid at rest. (a) Sound source at rest, w = 0. (b) Sound source moving at subsonic velocity, w = a12. (c) Sound source moving at sonic velocity, w = a.
2-14a, the center of which is shifted by x0 on the negative axis from that of the unit circle and which passes through the point z = a, a profile is produced that resembles a symmetric airfoil shape. It encircles the slit from -2a to +2a. This a symmetric Joukowsky profile, the thickness t of which is determined by the location xo of the center of the mapping circle. The profile is tapers toward the trailing edge with an edge angle of zero. Circular-arc profiles are obtained when the center of the mapping circle lies on the imaginary axis (Fig.