By Kirill V. Rozhdestvensky
This publication describes a mathematical version of stream previous a lifting procedure appearing regular and unsteady movement in shut proximity to the underlying stable floor (ground).
The writer considers numerous approximations according to the final approach to matched asymptotic expansions utilized to lifting flows. specific value is hooked up to the case of maximum floor results describing very small relative floor clearances. Practitioners occupied with the layout of wing-in-ground impression autos will locate during this publication the entire suitable formulae and calculated facts for the prediction of aerodynamic features during this vital restricting case. extra regularly, this publication is appropriate for graduate scholars, researchers and engineers operating or lecturing within the zone of theoretical aerodynamics.
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Extra info for Aerodynamics of a Lifting System in Extreme Ground Effect
58), take different magnitudes above and below the wing (btf:b2", bj ;t:b3"). 5), which complies with the requirement for the continuity of pressure and normal velocity across the wake in the immediate vicinity of the trailing edge. We will show how to ensure realization of this condition for a thin edge (eu = el = e), and then results will be presented for the trailing edge with finite vertex angle. The expression for pressure coefiicient in the adopted moving co ordinate system x, y, z can be calculated with the asymptotic error of the order of O(h~) as 8
In the vicinity of the edges of the wing (h and l2) and the wake l3, one has to derive local asymptotic descriptions of the fiow. Inspection of the Laplace equation shows that for sufficiently large radii of curvature of planform contours (Pe» h o), the flow near the edge can be 30 2. Problem Formulation considered two-dimensional in the plane normal to the planform contour. This circumstance considerably facilitates the analysis of edge flows. ). Examples of various edge flows are shown in Fig.
3. Local fiow solutions are constructed near the edges, depending upon the geometry and particulars of the physical performance of the latter. 58). 11). 106) where S is the reference area of the wing related to its root chord squaredj >. and l are the aspect ratio and relative span of the wingj and p- and p+ are 44 2. 103). Analyzing expressions for pressure, it is easy to see that for the upper surface of the wing, the corresponding formula is linearized, whereas for the lower surface a nonlinear formula is used.
Aerodynamics of a Lifting System in Extreme Ground Effect by Kirill V. Rozhdestvensky