Aerodynamics for engineering students - part 10 docx

... back for y in terms of Mo, my and t gives 1 m 1 m G = T [(Mo - &)(l - ~{Mo - lizt))]; =-[ M(l -1 nM) -Mo(l -1 nMo)l where M = MO - mt. Thus finally 1 G = [(M - ... of (v - V - ;ST/?. The total forward momentum is then 1 2 Now, by the conservation of momentum of a closed system: H2 = (M - rizbt)( V + SV)...

Ngày tải lên: 08/08/2014, 11:21

... high-speed tunnel at Guidornia, Atti Guidornia, No. 17, September 1939. 380 Aerodynamics for Engineering Students 1. 0- - Flat plate Favourable pressure gradient 0. 8- 0.6 - '\ ... pressure 364 Aerodynamics for Engineering Students L$t coefficient 4a CL =- drn For M = 1.72 CL = 2.86a Drag (wave) coefficient /' [ (0...

Ngày tải lên: 08/08/2014, 11:21

... This equation is F - A = P(;) Hence [ML-'T-2] = [p][LT-'L-'] = /p][T-'] Thus [p] = [ML-lT-'] and the units of p are therefore kgm-ls-l; in the SI system ... 78 83 83 83 84 85 86 86 87 87 89 89 91 91 95 95 96 97 101 104 104 104 105 106 107 109 110 110 112 Contents Preface xlll 1 Basic concepts and defdti...

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... direction. For three-dimensional flows Eqns (2.45) and (2.46) are written in the forms: 1 at ax ay az (ax ay az ap ap ap ap au av aw -+ u-+v-+w-+p -+ - +- =o au av aw -+ - +-= o ax ... becomes -6 xSy aP x 1 at Equating (2.42) and (2.43) gives the general equation of continuity, thus: aP a(Pu) a(P.1 - 0 -+ - + at ax ay This can...

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... Putting the line along the x-axis as $ = 0 128 Aerodynamics for Engineering Students Doublet axis Fig. 3.20 Streamlines due to a doublet - 2c - -x- Fig. 3.21 Consider again ... - In - = - In - * Here TO is the radius of the equipotential q5 = 0 for the isolated source and the isolated sink, but not for the combination. 1...

Ngày tải lên: 08/08/2014, 11:21

... dx H = -Jhge where p = pUk and x’ = x - (1 - F)c. Putting C C c x/ =-( i -cose) (i-cos~) =-( cos~-cose) 2 2 2 and k from Eqn (4.51): +,( (1 -; ) COS4Il - (1 where ... corresponding to x = pc. Two-dimensional wing theory 207 -Accurate computation 0 Experimental data Thin-aerofoil theory a 64panels -1 .00 -2 0 -1 5 -1...

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... cOsel = cose2 = - &x - Xd2 + (2 - x - x1 J(x - + (z + sz - z1)2 z + sz - 21 COS e2 + - = - sin02 = (2 J(x - + (2 + sz - The binomial expansion, i.e. ... 10 0-1 65; and a review by J.L. Hess (1990) ‘Panel methods in computational fluid dynamics’, Ann. Rev. Fluid Mech, 22, 25 5-2 74. 250 Aerodyn...

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... v2 u2 -+ - +- 2 7-1 2 y-1 Pmiq I Fig. 6.37 (a) 'Incompressible' flow. (b) Compressible subscritical flow. (c) Critical flow 324 Aerodynamics for Engineering Students ... Rankine- Hugoniot relations Eqn (6.42): -= or rearranged For air -/ = 1.4 and p2 6M: P1 5+M? -= - Reversed to give the ratio in terms of the exit Mach numbe...

Ngày tải lên: 08/08/2014, 11:21

... Aerodynamics for Engineering Students Pi 0.9 0.8 0.7 - 0.6 0.5 - 0.4 - 0.3 - - - U - 0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 1.0 0.9 0.8 0.7 - 0.6 0.5 - 0.4 - 0.3 - - - ... x lo6 440 Aerodynamics for Engineering Students So that Eqn (7 .105 ) becomes where we have written (7 .106 ) dii - aii...

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... a = 4 - 2e - 2d - f b = 2 - d - 2e - f c=l-e Substituting these in Eqn (9.15) gives T= c~ 4-2 -2 d-f 2-d-2e-f I-e d e f n p VKV = CpnZD4f [(z)d(L)e (-3 f] D2n pD2n2 ... [(L)"(T)-b(ML-3)c(L2T-1)d(ML-'T-2)e(LT-1~] Separating this into the three fundamental equations gives (M) I=c+e (L) 1 =a-3c+2d-e+f (T) 2=b+d+2e+f (...

Ngày tải lên: 08/08/2014, 11:21