By Kirill V. Rozhdestvensky
This ebook is devoted to the reminiscence of a unusual Russian engineer, Rostislav E. Alexeyev, who was once the 1st on the earth to strengthen the most important floor impact computing device - Ekranoplan. one in all Alexeyev's layout thoughts with the aerodynamic configuration of a jlying wing may be obvious at the entrance web page. The ebook offers an outline of a mathematical version of stream previous a lifting approach, acting regular and unsteady motions in shut proximity to the underlying stable floor (ground). this example is attention-grabbing for sensible reasons simply because either the aerodynamic and the industrial potency of the approach close to the floor are so much mentioned. Use of the strategy of matched asymptotic expansions permits closed shape ideas for the aerodynamic features of the wings-in-ground impact. those can be utilized for layout, id, and processing of experimental facts during constructing flooring impact cars. The time period severe flooring influence, wide-spread via out the e-book, is linked to very small relative floor clearances of the order of 10% or much less. the speculation of a lifting floor, relocating in instant proximity to the floor, represents one of many few proscribing situations that may be handled analytically. the writer wish to recognize that this paintings has been inspired via the guidelines of Professor Sheila E. Widnall, who was once the 1st to use the matched asymptotics recommendations to regard lifting flows with the floor impact. Saint Petersburg, Russia February 2000 Kirill V. Rozhdestvensky Contents 1. creation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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Extra info for Aerodynamics of a Lifting System in Extreme Ground Effect
As a result, as a consequence of limited computer resources, extremely elongated numerical cells appear near the body surface, causing ill conditioning of corresponding systems of equations and breakdown of most of the solvers; see Larsson . In spite of the progress envisaged in numerical solution of Navier-Stokes equations with the use of large eddy simulation (LES), and ultimately through direct numerical simulation (DNS), the experts do not expect that these methods would be realized earlier than 10 and 20 years, respectively.
3 Flow Above the Lifting System and Its Wake In the upper flow field Du, where (x, Y, z) = 0(1) for ho -+ 0 and e = O(h o), both the wing and the wake approach the ground. In the limit, one comes in the upper half space to the problem for the flow, generated by the tangency conditions on the upper surfaces of the wing and the wake. , the relative ground clearance, angle of attack, curvature and thickness of the wing are small) the upper flow can be linearized, so that tangency conditions are satisfied upon the projections of the wing and wake sheet onto the plane Y = o.
On the other hand, in the expression für trailing edge flow velo city potential 'Pte pass to the variable 1/ = hoh;ev and set h o (h;e) to zero for fixed 1/ and fj = 1 + O. 54) with du replaced byeu , 'Pte -+ 'Pteu rv h;b1e u ( In 1 h7r1/ ---,;;-1/ h. 79) 40 2. 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.