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Boundary layer flow under a peripheral jet in forward flight

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1 CHAPTER I INTRODUCTION A ground effect machine, abbreviated as GEM in the follow- ing, is a large-clearance fluid…
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2 interaction between the jets and the moving ground is also of importance in determining the trend of the base pressure as…
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3 . 5 will decrease more in fully than in partially simulated forward f1~ght. This pressure decrease cannot be neglected in…
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4 CHAPTER II THE FLOW AROUND A TWO-DIMENSIONAL PERIPHERAL JET A picture of the flow in the immediate vicinity of a two-…
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5 shown in Fig. 1, creates a front stagnation point a/ . The presence of this stagnation point can be explained only by…
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6 stagnation point ~ relative to the leading edge of the peripheral jet platform. To achieve this end, one may focus his…
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7 B.· The Effect of the Moving Wall The portion of the front jet deflected toward the rear has the dividing stagnation…
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8 C. The Sealing Capacity of the Rear Jet The rear jet curtain impinges at the point b on the portion of the front jet which…
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9 in wake pressure is more pronounced for a flying vehicle in an enclosed 8 guideway than for a vehicle in free flight.…
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ground. This indicates that the base pressure will decrease more in fully than in partially simulated forward flight. D.…
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11 CHAPTER III A SINGULAR PERTURBATION SOLUTION The flow problem to be considered below is depicted in Fig. 2, where a…
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12 where )y is the stream function. Observing equation (III-l))we can write the vorticity transport equations together with…
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13 or 1. I ] "'-/ 0 [ -:6 'tt} ~. .J..,I For ~O < I we must have »(! ) 2- For the flow to be laminar…
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14 A first integral yields (Van Dyke op. cit. p. 10) where WI is the vorticity. Under the assumption that the jet is ir-…
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15 i. e. , Integration of (111-8) yields the following (III-9) The arbitrary function f(X) in equation (111-9) is…
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16 CHAPTER IV A SERIES SOLUTION TO THE BOUNDARY LAYER EQUATION A. A Series Solution A series solution to the boundary layer…
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of powers of ? n..., we obtain For 7J1.., a -0 ' d- o=::,/ YL~O./ =d..1 ./ +11. (ro) = at'\.., h.. ~o { +n…
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18 B. Universal Functions The boundary conditions -f~( cc) ::: an.. ' n 2' 0 in equation (IV-S) are determined by…
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L ( I ) 1+L: /2 _.J.... r J)r 2 '22.. = - r; 2.. f\ r, (c) 1=;2. (D) =- f";J.{ (0) = "G.; ( CO) = 0 (d…
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while the inviscid external flow takes the form We consider the series solution in equation (IV-12) for a simple ex- ternal…
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21 CHAPTER V AN APPROXIMATE SOLUTION A. The Momentum Integral Equation The boundary layer equation may be transformed by…
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22 where 7 = ~)() and ~(.:G) is the nominal boundary layer thickness. The coefficients CZL(~) are determined by the…
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23 parameter a2(x) will be referred to as the "pressure gradient parameter" because it depends upon the inviscid…
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24 D. The Nominal Boundary Layer Thickness In the present problem, attention is focussed on the nominal boundary layer…
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25 For a o ~ 0, the corresponding range of a 2 is as follows However, the existence of a maximum or a minimum in the…
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