Question

Air flows from a reservoir where P 300 kPa and T 500 K through a throat to section 1 in Fig. 3.4, where there is a normal shock wave. Compute (a) Pi (b) P2 (c) Po2 (d) A 2 (e) Po3 (f)A* (g) P3 (h) To3 Air Reservoir Po 300 kPa 12 13 T01-500 K | Shock P100 psia

Answer 1

0 Compute P toho M1 Mach Number f shock wa e can t exist unless M, s súpevsơmic . Hence, flo accelendtas thonaugh oaohich is sonic Hance, rom is sentbopic 30o kfa 28.06 kra B = 28.06 kPa ts evalualaJ bi uwing inMi and Ney mal Shock -table a/p P - 5.48

cn 2 = 5.48 XP, fom above R 28,06 KPa B. = 5.48 x 28,06ニ153A3 ay conside in 0, 19 -ficm -tha Novnl shock table -fu m 2.2 32 O, G28x 300 a) ที่ A, 佐 1.512 3 Ce Shock

du오 to flow -from sechơn 2 to 3 Isentropic ·丹 Tre ponure B s calculated by crnaldring Paa the M3 s subsonic. due do doonsneam Shock Pressure is follocos -fm 는-1,078 3 i.078- 3 = 188 I , 078 Pg = 174.39 1S92 m thnoughout -ha duct -the -flocos odiabatc 500 k 03 dua o adiabaic -floao ·T63 103 -LO22. T3 S00/1,022 489 k 3 T3 489 K