Fluid Mechanics: Fundamentals and Applications
4th Edition
ISBN: 9781259696534
Author: Yunus A. Cengel Dr., John M. Cimbala
Publisher: McGraw-Hill Education
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Chapter 12, Problem 157P
To determine
The nozzle exit velocity.
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It is proposed that a nozzle receive air at 2 m/s, 300 K, and 150 kPa, attemperature of 280 K, and a velocity of 100 m/s. The mass flow rate is 0.1 kg/s. The surface of the nozzle is kept at 270 K. Assuming that the air behaves as an ideal gas with constant specific heats. Is this process possible?Given: Vel1 = 2 m/s, T1 = 300 K, P1 = 150 kPa, Vel2 = 100 m/s, T2 = 280 K, P2 = 110 kPa, dm/dt = 0.1 kg/s, Cp,air = 1.005 kJ kg-1 K-1
A large reservoir maintains air at 6.8×105 P a and 15°C. The air flows isentropically through a convergent and divergent nozzle to another large reservoir where the back pressure can be varied. The area of the throat is 25 cm2 and the area of the nozzle exit is 100 cm2 . Find (a) The maximum mass flow rate through the nozzle. (b) The two values of the Mach number at the nozzle exit corresponding to this mass flow rate. (c) The back pressures required to produce these Mach numbers.
Consider a converging nozzle with sonic speed at the exit plane. Now the nozzle exit area is reduced while the nozzle inlet conditions are maintained constant. What will happen to (a) the exit velocity and (b) the mass flow rate through the nozzle?
Chapter 12 Solutions
Fluid Mechanics: Fundamentals and Applications
Ch. 12 - What is dynamic temperature?Ch. 12 - Calculate the stagnation temperature and pressure...Ch. 12 - Prob. 6PCh. 12 - Prob. 7PCh. 12 - Prob. 8EPCh. 12 - Prob. 9PCh. 12 - Products of combustion enter a gas turbine with a...Ch. 12 - Is it possible to accelerate a gas to a supersonic...Ch. 12 - Prob. 72EPCh. 12 - Prob. 73P
Ch. 12 - Prob. 74PCh. 12 - Prob. 75PCh. 12 - For an ideal gas flowing through a normal shock,...Ch. 12 - Prob. 77CPCh. 12 - On a T-s diagram of Raleigh flow, what do the...Ch. 12 - What is the effect of heat gain and heat toss on...Ch. 12 - Prob. 80CPCh. 12 - Prob. 81CPCh. 12 - Prob. 82CPCh. 12 - Argon gas enters a constant cross-sectional area...Ch. 12 - Prob. 84EPCh. 12 - Prob. 85PCh. 12 - Prob. 86PCh. 12 - Prob. 87EPCh. 12 - Prob. 88PCh. 12 - Prob. 89PCh. 12 - Prob. 90PCh. 12 - Prob. 91PCh. 12 - Prob. 93CPCh. 12 - Prob. 94CPCh. 12 - Prob. 95CPCh. 12 - Prob. 96CPCh. 12 - Prob. 97CPCh. 12 - Prob. 98CPCh. 12 - Prob. 99CPCh. 12 - Prob. 100CPCh. 12 - Prob. 101PCh. 12 - Air enters a 5-cm-diameter, 4-m-long adiabatic...Ch. 12 - Helium gas with k=1.667 enters a 6-in-diameter...Ch. 12 - Air enters a 12-cm-diameter adiabatic duct at...Ch. 12 - Prob. 105PCh. 12 - Air flows through a 6-in-diameter, 50-ft-long...Ch. 12 - Air in a room at T0=300k and P0=100kPa is drawn...Ch. 12 - Prob. 110PCh. 12 - Prob. 112PCh. 12 - Prob. 113PCh. 12 - Prob. 114PCh. 12 - Prob. 115PCh. 12 - Prob. 116EPCh. 12 - A subsonic airplane is flying at a 5000-m altitude...Ch. 12 - Prob. 118PCh. 12 - Prob. 119PCh. 12 - Prob. 120PCh. 12 - Prob. 121PCh. 12 - Prob. 122PCh. 12 - Prob. 123PCh. 12 - An aircraft flies with a Mach number Ma1=0.9 at an...Ch. 12 - Prob. 125PCh. 12 - Helium expands in a nozzle from 220 psia, 740 R,...Ch. 12 - Prob. 127PCh. 12 - Prob. 128PCh. 12 - Prob. 129PCh. 12 - Prob. 130PCh. 12 - Prob. 131PCh. 12 - Prob. 132PCh. 12 - Prob. 133PCh. 12 - Prob. 134PCh. 12 - Prob. 135PCh. 12 - Prob. 136PCh. 12 - Prob. 137PCh. 12 - Prob. 138PCh. 12 - Air is cooled as it flows through a 30-cm-diameter...Ch. 12 - Prob. 140PCh. 12 - Prob. 141PCh. 12 - Prob. 142PCh. 12 - Prob. 145PCh. 12 - Prob. 148PCh. 12 - Prob. 149PCh. 12 - Prob. 150PCh. 12 - Prob. 151PCh. 12 - Prob. 153PCh. 12 - Prob. 154PCh. 12 - Prob. 155PCh. 12 - Prob. 156PCh. 12 - Prob. 157PCh. 12 - Prob. 158PCh. 12 - Prob. 159PCh. 12 - Prob. 160PCh. 12 - Prob. 161PCh. 12 - Prob. 162PCh. 12 - Assuming you have a thermometer and a device to...
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- Air enters a turbine at temperature and pressure of 800°C, 10bar respectively. The actual exit airtemperature is 180°C. The turbine isentropic efficiency is estimated to be 85%. Calculate the turbine exit pressure and the actual expansion index (n).arrow_forwardi need the answer quicklyarrow_forwardConsider an aircraft engine operating at subsonic conditions with a nozzle that has an exit area of 142in2 and a nozzle inlet/exit area ratio of 2. Engine gases flowing at 30lbm/s enter the nozzle with a pressure of 0.83 bar and avelocity of 144 m/s. The gases expand through the nozzle, exiting at the ambient pressure of 7.25 psia with a velocity of 1320 ft/s. a) For these conditions, what is the force (in units of lbf) trasmitted to the structure holding the nozzle. Provide both direction and magnitude of the force. b) Based on your results, comment on whether the force acting on the nozzle would hlep speed up or slow down a vehicle that used this nozzle as part of a jet propulsion system. I mostly wanted help in part b. Thank you.arrow_forward
- With a negligible velocity, air at 900 kPa and 400 K enters a converging nozzle. The nozzle's throat area is 10 cm2 (Figure Q1). Considering and stating the necessary assumptions, (a) calculate the exit pressure, exit velocity, and mass flow rate vs the back pressure Pb for 0.9 ≥ Pb ≥ 0.1 MPa, assuming the flow is isentropic. (b) Plot the graph of the exit pressure, exit velocity, and mass flow rate vs the back pressure Pb. Properties: The properties of air are k = 1.4, R = 0.287 kJ/kg·K, and cp = 1.005 kJ/kg·K.arrow_forwardConsider a converging nozzle and a converging– diverging nozzle having the same throat areas. For the same inlet conditions, how would you compare the mass flow rates through these two nozzles?arrow_forwardSteam at an initial enthalpy of 100 kJ/kg and inlet velocity of 100 m/s, enters an insulated horizontal nozzle. It leaves the nozzle at 200 m/s. The exit enthalpy (in kJ/kg) is.arrow_forward
- Thermodynamics: Please show how to solve the given problem and how to find the answer step by steparrow_forwardSolve fast..arrow_forward1- Nitrogen is stored in a large chamber under conditions of 450 K and 1.5 x 105 N/m . The gas leaves the chamber through a convergent-only nozzle whose outlet area is 30 cm .The ambient room pressure is 1 × 105 N/m, and there are no losses. (a) What is the velocity of the nitrogen at the nozzle exit? (b) What is the mass flow rate? (c) What is the maximum flow rate that could be obtained by lowering the ambient pressure? ERING RINCarrow_forward
- A jet engine at 7000m altitude takes in 45 kg/s of air and adds 550 kJ/kg in the combustion chamber. The chamber cross section is 0.5 m2 and the air enters the chamber at 80 kPa and 5oC. After combustion the air expands through an isentropic converging nozzle to exit at atmospheric pressure. Estimate (a) the nozzle throat diameter (b) the nozzle exit velocity and (c) the thrust produced by the engine.arrow_forwardSend paper solution solve allarrow_forwardConsider gas flow through a converging nozzle with specified inlet conditions. We know that the highest velocity the fluid can have at the nozzle exit is the sonic velocity, at which point the mass flow rate through the nozzle is a maximum. If it were possible to achieve hypersonic velocities at the nozzle exit, how would it affect the mass flow rate through the nozzle?arrow_forward
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