Question

Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the shock appears? (c) Find the mass flow rate through the nozzle. (d) Find the back pressure (Pb). Region 2 (e) Find the back pressure (Pb) for a design condition where the flow at the exit is supersonic without any shock occurring in the nozzle and outside of the nozzle. Region 1

Answer 1

Answer:

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Answer :- Mach Number upstream to the shock to of Mach No given that Mag = 16405 according to this, to this, corrosponding this Mach Number: from the table Mach No for Mai=1.70 Answer. upstream (bi that A* = 3cm² ginen as we know that 3 A shock (1+: 2Mål 1.728 May Now as we have all the valus and putting in the equation Ashock = A*(1 + 2 Mai) 1.728 Ma, At 3 Ashock - 3 (1+ 2x1.7 +2X]:72) 1.728 x 1.7 A shock = 4:01x10-2 m² 4.01cm2

(0) Mass flow rate mass flow rate can be ginen mi= .68478 PO A * FRTO 2.6847 X 500X103x H.01x10 4 ✓ 2870 350 ni 13728, 2010 +43-3 kg/see 316.93 m =.4 3 3 kg 1sec at throat -2 (d) Me= '43342 866 6kg/s at enit Back Pressure : Before and after shock the table from we can find the ratio 5:2026, P, 212026 x 500 kPa Po 101.3 kPa 3.205 PI at (Ma, = 17) P2=3.205x1013 P22 325 kPa again from table P2 Auswer