By Holt Ashley
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Additional resources for Aerodynamics of Wings and Bodies
Direction, determined as a line paraIIel to one between the center of the circle in the s-plane and the point HI which transforms into the airfoil trailing edge. , when the radius a of the circle becomes equal to a quarter of the chord. ), a moment axis about which the pitching moment is independent of angle of attack. This point is iocated on the Z-plane as shown in Figs. 53 of Milne-ThompsQft (1960). The moment about the aerodynamic center is (2-160) where at = (l e-i'Y) 2. 2 (2-158) (2-161) Figure 2-18 gives some indication of the accuracy with which lift and moment can be predicted.
For a thorough discussion of higher-order boundary layer approximations, the reader is referred to Van Dyke (1964). 5 Thin-wing Theory 5-1 Introduction In this chapter we shall derive the equations of motion governing the sub- or supersonic flow around thin wings. Although this problem may be handled by simpler regular perturbation methods, we shall here instead use the method of matched asymptotic expansions for basically two reasons. First, the present method gives a clearer picture of the usual linearized formulation as that for an outer flow for which the wing in the limit collapses onto a plane (taken to be z = 0).
In th& separated flow there will always be a turbulent wake . Unseparated Row Separated Row (a) (b) FIG. 4-1. Examples of high Reynolds number flows. Asterisks indicate regions in which viscosity is important. behind the body. In principle one could have instead a region of fairly quiescent flow in the wake, separated from the outer flow by a thin laminar shear layer attached to the laminar boundary layer on a body. However, a free shear layer, lacking the restraining effect of a wall, will be highly unstable and will therefore turn turbulent almost immediately.
Aerodynamics of Wings and Bodies by Holt Ashley