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

... 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...

Ngày tải lên: 08/08/2014, 11:21

... 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...

Ngày tải lên: 08/08/2014, 11:21

... 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...

Ngày tải lên: 08/08/2014, 11:21

... 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...

Ngày tải lên: 08/08/2014, 11:21

... 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