By W. L. Shields (auth.), John H. Olsen, Arnold Goldburg, Milton Rogers (eds.)
The mix of accelerating airport congestion and the advert vent of enormous transports has prompted elevated curiosity in airplane wake turbulence. A quantitative knowing of the interplay among an plane and the vortex wake of a previous airplane is critical for making plans destiny excessive density air site visitors styles and keep watch over platforms. the character of the interplay is determined by either the features of the next plane and the features of the wake. many of the inquiries to be replied are: What deter mines the whole features of the vortex wake? What homes of the subsequent airplane are very important? what's the function of pilot reaction? How are the wake features relating to the genera ting plane parameters? How does the wake crumble and the place? a lot of those questions have been addressed at this primary plane Wake Turbulence Symposium subsidized via the Air strength workplace of Sci entific learn and The Boeing corporation. employees engaged in aero dynamic study, airport operations, and software improvement got here from a number of count number ries to offer their effects and alternate info. the recent effects from the assembly supply a present photograph of the country of the data on vortex wakes and their interactions with different airplane. Phenomena formerly considered as mere curiosities have emerged as very important instruments for figuring out or controlling vortex wakes. the hot sorts of instability taking place in the wake might at some point be used for selling early dis integration of the damaging dual vortex structure.
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Additional resources for Aircraft Wake Turbulence and Its Detection: Proceedings of a Symposium on Aircraft Wake Turbulence held in Seattle, Washington, September 1–3, 1970. Sponsored jointly by the Flight Sciences Laboratory, Boeing Scientific Research Laboratories and the Air F
5) gives then the mass conservation equation as dF dt -= - (7) GVw assuming again that density changes are small over the distance traveled. When the vortex system has acquired buoyancy, the circulation about each vortex is altered by the buoyancy. The circulation equation for inhomogeneous fluids (the Bjerkness equation) is 9 dr dt =- (8) where C is the contour along which the circulation is computed. For the present application, take C as shown in Fig. 2, so that legs 1 through 3 are entirely in the ambient atmosphere and leg 4 bisects the oval along the line of symmetry between the vortices.
18), (19) In particular the behavior of ;'(0) as r - co is ~nd (20) remains valid. 3 (t) will be related to the boundary condition at r = 0 after the determination of the vorticity distribution ,(0). From eq. (37a) the matching condition of eq. (35b) yields R (t) = o w* (t,R ,Z ) 1 0 (40) 0 Eqs. (38) and (39) and the matching conditions of eqs. n(8R/E) -1 + ~ (t)} (41) -1 on ~ while the term Ga (t)r in eq. (39) will induce o an extra term in the outer solution of the order E-a . he Ring and the Vorticity Distribution Equation (36) is an ordinary differential equation in r for *(l)(t,~) with t appearing as a parameter, therefore, for each preII scribed vorticity distribution at each instant *(1) can be deter11 mined by eq.
66b) W(s ,r 9, t, e) W(1) (s, r, 9 , t) + Ew(2) +... (66c) = In order to later on balance the leading terms of the momentum equations, the following expansion of pressure p(s,r,9,t,E) is assumed, - _ p - E -2- (0) P + E -1- (1) P + - (2) P +... (67) Since the vortex line is assumed to move with finite velocity the following expansion is introduced, -;l. _ ..... (s, t, e) - X -> (s, t) + EX (1) (s, t) +... (68) The geometrie par~meters, k- 1 , T and h1 can be expanded likewise and related to X(1)(S,t).