Aerodynamics for engineering students - part 8 pps

... [35.5p5f8 x 16 480 + 55 .8 x lo5 - 55 .8 x I05pj4f5 55 .8 x 105 i.e. 55 .8 465 5f4 - 55 .8 x lo5 = (35.6 - 55 .8) 105 ( 0.1 488 ) 5 .84 - 55 .8 x 1oSp = or 55 .8~ - 5 .84 ~~1~ ... 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...

Ngày tải lên: 08/08/2014, 11:21

... 3.3 Two-dimensional flow from a source (or towards a sink) 52 52 52 53 54 56 56 62 62 62 64 64 66 68 68 71 72 73 73 75 76 78 83 83 83 84 85 86 86 87 87 89 89 91 ... 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 th...

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 ... second. 68 Aerodynamics for Engineering Students Therefore, true air speed = Ma = 0.7 28 x 340.3 2 48 m s-' = 89 1 km h-' In this ex...

Ngày tải lên: 08/08/2014, 11:21

... Putting the line along the x-axis as $ = 0 1 28 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....

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 ... inclined at angle Q to Ox 1 78 Aerodynamics for Engineering Students The lift per unit span = apU2clT(l +cosO)dO = 7i-apU2c It therefore follows that for u...

Ngày tải lên: 08/08/2014, 11:21

... 5.1 7~ /8 0. 382 68 0.923 88 0.923 88 0. 382 68 0.923 88 ~14 0.707 11 0.707 11 -0 .707 11 -0 .707 11 0.707 11 3~ 18 0.923 88 -0 . 382 68 -0 . 382 68 0.923 88 0. 382 68 7512 1 .ooo 00 - 1 .ooo ... 0 .89 202 A3 + 1.251 00 A5 + 0.66 688 A7 0.011637 = 0.663 19 A1 f0. 989 57 A3 - 1.315 95A5 - 1.64234 A7 0.0216 65 = 1.1 15 73 A1 -...

Ngày tải lên: 08/08/2014, 11:21

... Aerodynamics for Engineering Students Now for values of MI near unity /3 << 1 and = 1 - e-P APO -Pol - Po2 Po1 Pol ~ APO - 2n' (M: - 'I3 (as before, Eqn (6.55)) ... v2 u2 -+ - +- 2 7-1 2 y-1 Pmiq I Fig. 6.37 (a) 'Incompressible' flow. (b) Compressible subscritical flow. (c) Critical flow 324...

Ngày tải lên: 08/08/2014, 11:21

... 0.104 0.00 08 -0 . 083 1 -0 .1166 -0 .1474 -0 .1754 WP)li7l 0.2 28 0. 183 0.1 38 0.092 0 -0 .0 98 -0 .1 38 -0 . 183 -0 .2 28 Wings of finite span When the component of the free-stream velocity ... 0.2 0.12 0.3 0. 08 0.5 0.0 0.7 -0 . 08 0 .8 -0 .12 0.9 -0 .16 1.0 -0 .20 e 11.31" 9.09" 6 .84 " 4.57" 0.0...

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

... 0.2 680 0.2576 0.2477 0.2 381 0.2 289 0.2200 0.21 15 0.2034 0.1955 0. 187 9 0. 180 7 0 .88 08 0 .87 60 0 .87 13 0 .86 65 0 .86 17 0 .85 68 0 .85 20 0 .84 71 0 .84 23 0 .83 74 0 .83 25 0 .82 76 0 .82 27 ... 0 .81 77 0 .81 28 0 .80 78 0 .80 28 0.79 78 0.79 28 Constant in stratosphere Constant in stratosphere 1.7303 1.7702 1 .81 13 1 .85 36 1 .89...

Ngày tải lên: 08/08/2014, 11:21