Consider a rocket engine burning hydrogen and oxygen. The total mass flow of the propellant plus oxidizer into the combustion chamber is 287.2 kg/s. The combustion chamber temperature is 3600 K. Assume that the combustion chamber is a low-velocity reservoir for the rocket engine. If the area of the rocket nozzle throat is
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HEAT+MASS TRANSFER:FUND.+APPL.
Introduction to Heat Transfer
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- automobile is traveling at 55 mph on a highway. The car's engine is operating at 2000 revolutions minute. The engine fills its cylinders with air each time two per revolutions are completed, i.e., it operates on a four-stroke cycle. The volume of air ingested during each cycle is 95% of the engine's displacement of 1.5 liters. The air enters the cylinders at 0.7 atm and 305 K. Determine the following: The volumetric flow rate of the air at the entering conditions. Calculate in units of m'/s and ft'/min (CFM). А. 3 The mass flow rate of the air (kg/s). B. bas The volumetric flow rate of the air at standard temperature and pressure С. 3 (STP = 101.325 kPa and 298.15 K). Calculate in units of m'/s and ft'/ min (SCFM).arrow_forward100% High pressure water and compressed air are delivered to some operating rooms. Bored one day, with no patients around, you take the cap off the nozzle to see what would happen. Water flows through the vertical pipe and nozzle and then exhausts into the air as shown in the diagram. The water pressure in the pipe at position 1 is 3 atm. The pressure when the water discharges to the air is 1 atm. Position 2 identifies the nozzle, 0.75 m above position 1, where the water flow has been constricted from an 8-cm diameter pipe to a 3-cm diameter nozzle. Assume that the free jet remains a stream of water with a 3-cm diameter. Assume no friction losses. Free jet -3 cm diameter 0.75 m a) Determine the mass flow rate of water through pipe at position 1 in kg/s. 3 atm 8 cm diameter b) Determine the height, h, the water jet can rise. c) Calculate the friction factor inside the 8-cm pipe and determine if the assumptions of negligible friction losses was reasonable. Water AR d 128 PM 10/3/2021…arrow_forwardCalculate the thrust of a turbojet engine with an inlet diameter of 4 ft. If an airplane is flying at altitude of 15km at Mach 0.8 with an exit velocity of 900ft/s. The turbojet engine thrust at 15-km. (in Lbf)arrow_forward
- A steady stream of n-butanol is needed to be fed into the reactor at 40 ̊C. However, the inlet of the reactor is located 7.5 m above the reservoir tank. As such, a highly effective centrifugal pump (70% efficiency) is used for such a purpose. It was understood that the needed volumetric flow rate into the reactor is fixed at 20 m3/h. It was also noted that the n-butanol reservoir is closed but not pressurized, while the gauge pressure at the endof the discharge line is measured at 275 kPa. Given that the density of n-butanol is 810kg/m3. If the discharge pipeline was 5 cm in diameter, calculate: (i) The velocity of n-butanol at the discharge line. (ii) The total power input from the centrifugal pump. (iii) The power delivered to the n-butanol fluid.arrow_forward4. Carbon dioxide flows steadily through a varying cross-sectional-area duct such as a nozzle at a mass flow rate of 3 kg/s. The carbon dioxide enters the duct at a pressure of 1400 kPa and 200°C with a low velocity, and it expands in the nozzle to a pressure of 200 kPa. The duct is designed so that the flow can be approximated as isentropic. Determine the following parameters at each location along the duct that corresponds to a pressure drop of 200 kPa: (i) density; (ii) velocity; (iii) flow area; (iv) mach number. You may assume: • Carbon dioxide is an ideal gas with constant specific heats at room temperature; • Flow through the duct is steady, one-dimensional and isentropic. Use cp=…arrow_forward4. The diameter of the pipes (1) and (2) connected to the tank shown in the figure are 3 cm and the diameter of the pipe (3) is 6 cm. Alcohol with a density of 0.79 is injected into the tank from pipe (1) with a speed of 10 m/s and water is injected to tank from pipe (2) with a speed of 16 m/s. Assuming that there is an ideal mixture in the tank, find the exit velocity of the mixture in the pipe (3) and the specific mass of the mixture. Alcohol (1) (3) Admixture Ideal Mixture Water (2)arrow_forward
- A jet-propelled airliner flies at an altitude of 15,000 m and a velocity of 265 m/s. What is the stagnation pressure and stagnation temperature of the air entering the engine? If the airliner is stationary on the ground, the engines are running with the same Mach number flow into the engines, and the air flow to each engine is 35 kg/s, what is the airflow to each engine at the above flight conditions? Po = Pa To = i mf = K kg/sarrow_forwardSTELIA Aerospace are planning to design a spherical cryogenic tank to be stored with liquid hydrogen. It is also designed with a system that if the tank reaches maximum capacity all entry and exit nozzles will automatically be closed. The specific gravity of this fluid is approximately seven hundredths the density of water. The tank is designed to have two-entry filtration system and an exit nozzle located at the bottom. The liquid hydrogen flows into the cryogenic tank at a rate of 0.85 kilograms per second and 0.75 kilograms per second. At the same time the exit nozzle is opened with a rate of 0.005 kilograms per second. (a)The shutoff valves were closed after 35 minutes, what is the volume and radius of the spherical tank? (b) Using your answers on item a, how full is the tank (in percentage) after 27.15 minutes?arrow_forwardwater enters the mixer through pipe A at a flow rate of 200 L/s, while oilenters through pipe B at 45 L/s. A homogeneous mixture of oil globules in water isformed and leaves though pipe C with a diameter of 0.25 m. Find the averagevelocity and density of the mixture leaving through pipe C. The oil has density of 800kg/m3..arrow_forward
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