Aerodynamics for engineering students - part 7 docx

... 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& quot; 0.0 -4 . 57& quot; -6 .84" -9 .09" -1 1.31" ne 0" 2.22" 4. 47& quot; ... 0.104 0.0008 -0 .0831 -0 .1166 -0 .1 474 -0 . 175 4 WP)li7l 0.228 0.183 0.138 0.092 0 -0 .098 -0 .138 -0 .183 -0 .228 Wings o...

Ngày tải lên: 08/08/2014, 11:21

... 0.8082 0.8025 0 .79 69 0 .79 12 0 .78 56 0 .77 99 0 .77 43 0 .76 87 0 .76 30 0 .75 74 0 .75 17 Constant in stratosphere Constant in stratosphere 0.4344 0.4195 0.4050 0.3910 0. 377 3 0.3640 0.351 ... 0.8 471 0.8423 0.8 374 0.8325 0.8 276 0.82 27 0.8 177 0.8128 0.8 078 0.8028 0 .79 78 0 .79 28 Constant in stratosphere Constant in stratosphere 1 .73...

Ngày tải lên: 08/08/2014, 11:21

... = 273 °C and po = 1 .71 x kgm-ls-l (i) Full-scale aircraft M = 0.85, a = 20.05( 273 - 56.5)'12 = 297ms-' V = 0.85 x 2 97 = 252m s-' 71 60 = 0.1151 kgm-3 ... 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 .72 8 x 340.3 248 m s-' = 89 1 km h-' In this exampl...

Ngày tải lên: 08/08/2014, 11:21

... Therefore p-po=-pU 1- 2sin0f- 2 2[ ( 2rua >’ (3.49) Potential flow 129 Now and Therefore r; = x2 + y2 - 2xc + c2 m x2+y 2-2 xc+c2 47r x2 + y2 + 2xc + c2 $I=-ln ... - 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. 12...

Ngày tải lên: 08/08/2014, 11:21

... angle Q to Ox 178 Aerodynamics for Engineering Students The lift per unit span = apU2clT(l +cosO)dO = 7i-apU2c It therefore follows that for unit span I CL = ($q) =27ra The moment ... 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...

Ngày tải lên: 08/08/2014, 11:21

... Table 5.1 7~ /8 0.382 68 0.923 88 0.923 88 0.382 68 0.923 88 ~14 0 .70 7 11 0 .70 7 11 -0 .70 7 11 -0 .70 7 11 0 .70 7 11 3~18 0.923 88 -0 .382 68 -0 .38268 0.923 88 0.38268 75 12 1 .ooo 00 - 1 .ooo ... 0.00 473 9 = 0.22 079 A1 + 0.89202 A3 + 1.251 00 A5 + 0.66688 A7 0.0116 37 = 0.663 19 A1 f0.989 57 A3 - 1.315 95A5 - 1.64234 A7 0.02...

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 ... x0)x + [xo(C + XO) - A] = 0 (6.86) having the formal solution x=J [-( C+XO) f .\/(C+XO)( ~-~ XO) +4A] (6. 87) 306 Aerodynamics for Engineering Stud...

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 - - - ... method for laminar boundary layers is to use the approximate expressions (7. 64a’,b’,c’) with Eqn (7. 59) (or 7. 98) rewritten as (...

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