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Chapter 12 Solutions
Fox and McDonald's Introduction to Fluid Mechanics
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- Fluid mechanical A large vessel contains compressed air at To = 350 K and Po = 2 bar. A converging-diverging nozzle is attached to the vessel to discharge air. The throat area of the nozzle is 200 cm2. At the exit, the pressure is 20 kPa and the flow is supersonic. Answer the followings: The mass flow rate of the air = Mach number at exit = he exit are = Air velocity at exit Air velocity at throat = Air pressure at throat =arrow_forwardNUMBER 1; Consider a rocket engine burning hydrogen and oxygen; the combustion chamber (reservoir) pressure and temperature are 25 atm and 3517 K, respectively. The area of the rocket nozzle throat is 0.1m². The area of the exit is designed so that the exit pressure is equal to 0.01174 atm. Determine the exit area and exit velocity with the given parameters: Mass flow rate = 121.9 kgm/s Molecular weight (gas mixture) Specific heat ratio (gas mixture) = 1.22 Universal gas constant = 8,314 J/ (kg/mol) (K) = 16 molarrow_forward• A 50 litre tank takes 4 minutes to fill with petrol (density 733 kg/m3 ) through a nozzle of diameter 15 mm. What is the mass flowrate of petrol into the tank? What is the mean velocity of petrol leaving the nozzle?arrow_forward
- Two gaseous stream enter a combining tube and leave as a single mixture. The entrance data for one of the gas, A1=75 in2, v1=500 fps, V1=10 ft3/lb; for the other gas, A2=50 in2, m2=600 lb/hr, p=0.12 lb/ft3. At exit, v3=350 fps, V3=7 ft3/lb. Find the mass flow rate (in lb/hr) at the exit section. a. 157,800 b. None of these c. 140,200 d. 153,750 e. 94,351arrow_forward5. Two gaseous streams enter a combining tube and leave as a single mixture. These apply at the entrance section. Find the speed at section 2, the flow rate and area at section 3. data A1 = 75 in?, V1 = 500 fps, vị = 10 ft³/lb At exit: V3 = 350 fps, v3 = 7 ft³/lb ;A2 = 50 in?, ṁ2 = 16.67 Ib/s, p2 = 0.12 Ib/ft³arrow_forwardIn an air pipeline, the flow has the following conditions at section 1: 25°?, 1.9 bar, 20 m/s velocity, and 50 mm inside diameter of pipe. At section 2, the conditions are: 25°?, 1.4 bar, and 75 mm inside diameter of pipe. a. Calculate the mass flow rate of air. b. Determine the velocity at the section 2.arrow_forward
- Air flows through a converging-diverging (c-d) nozzle. It is supplied from a large air reservoir in which the temperature is 377 K and the pressure is 190 kPa. The velocity and the cross-sectional area at the nozzle exit are 462 m/s and 0.0005 m^2, respectively. Find the followings: Mach number at exit is Area of the throat is The mass flow rate of air is The exit temperature is The exit pressure isarrow_forwardPressurized water (pin = 10 bar, Tin =110◦C) enters the bottom of an L = 12m long vertical tube of diameter D = 110 mm at a mass flow rate of m =1.5kg/s . The tube is located inside a combustion chamber, resulting in heat transfer to the tube. Superheated steam exits the top of the tube at pout = 7 bar, Tout = 600◦C. Determine the change in the rate at which the following quantities enter and exit the tube: (a) the combined thermal and flow work, (b) the mechanical energy, and (c) the total energy of the water. Also, (d) determine the heat transfer rate, Q˙. Hint: Relevant properties may be obtained from a thermodynamics text.arrow_forward1arrow_forward
- Q1/1In a single-stage axial flow gas turbine of A319 Airbus Airplane has an axial velocity is equal to 250 m/s, and assume equal inlet and outlet velocities. Stage exit swirl angle is 9° , mass flow rate of gas is 15 kg/s, and nozzle efflux angle is 63°. Assume that blade speed is 350 m/s, gas enters at stagnation pressure of 5 bar, and stagnation temperature of 1980 °R. Also, assume y = 1.33, and C,,=1.147 kJ/kg. K. Determine the rotor blade gas angles, output power, blade-loading coefficient, and degree of reaction.arrow_forward26arrow_forwardhelp me please need solution through half hr please.arrow_forward
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