Fluid Mechanics: Fundamentals and Applications
4th Edition
ISBN: 9781259696534
Author: Yunus A. Cengel Dr., John M. Cimbala
Publisher: McGraw-Hill Education
expand_more
expand_more
format_list_bulleted
Question
Chapter 12, Problem 162P
To determine
Lowest pressure that will occur within the nozzle.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solutionStudents have asked these similar questions
2- Products of combustion enter a gas turbine with a stagnation pressure of 0.75
MPa and a stagnation temperature of 690 °C, and they expand to a stagnation
pressure of 100 kPa. Taking cp = 1.157 kJ/kg.K, k = 1.33 and R = 0.287 kJ/kg-K for the
products of combustion, and assuming the expansion process to be isentropic,
determine the power output of the turbine per unit mass flow.
Argon gas is approaching a converging–diverging nozzle with a low velocity at 20°C and 150 kPa, and it leaves the nozzle at a supersonic velocity. If the cross-sectional area of the throat is 0.015 m2, the mass flow rate of argon through the nozzle is (a) 0.47 kg/s (b) 1.7 kg/s (c) 2.6 kg/s (d ) 6.6 kg/s (e) 10.2 kg/s
QUESTION 6
Air enters a diffuser with an averaged velocity of 360 m/s at a
temperature of 340 kPa and 420 K and leaves at a stagnation pressure of 300 kPa with an
averaged velocity of 120 m/s and a static pressure of 285 kPa. Determine,
stagnation pressure and
(i) the static pressure and Mach number of the air at inlet;
(ii) the diffuser efficiency
(iii the Mach number at exit and the overall entropy increase
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...
Knowledge Booster
Learn more about
Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.Similar questions
- 4-Steam flows through a device with a stagnation pressure of 120 psia, a stagnation temperature of 7008F, and a velocity of 900 ft/s. Assuming ideal- gas behavior, determine the static pressure and temperature of the steam at this state.arrow_forward5- An aircraft is flying at an altitude of (12000 m) (T = 216.65 k, P = 0.193bar) at a Mach number of (0.82). The cross-sectional area of the inlet diffuser is (0.5 m2).Determine: (a) The mass of air entering the compressor per second. (b) The speed of aircraft. (c) The stagnation pressure and temperature of air at the diffuser entry.arrow_forwardCarbon dioxide enters a converging–diverging nozzle at 60 m/s, 310°C, and 300 kPa, and it leaves the nozzle at a supersonic velocity. The velocity of carbon dioxide at the throat of the nozzle is (a) 125 m/s (b) 225 m/s (c) 312 m/s (d ) 353 m/s (e) 377 m/sarrow_forward
- What would happen if we tried to further accelerate a supersonic fluid with a diverging diffuser?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_forwardConsider gas flow through a converging–diverging nozzle. Of the five following statements, select the one that is incorrect: (a) The fluid velocity at the throat can never exceed the speed of sound. (b) If the fluid velocity at the throat is below the speed of sound, the diversion section will act like a diffuser. (c) If the fluid enters the diverging section with a Mach number greater than one, the flow at the nozzle exit will be supersonic. (d ) There will be no flow through the nozzle if the back pressure equals the stagnation pressure. (e) The fluid velocity decreases, the entropy increases, and stagnation enthalpy remains constant during flow through a normal shock.arrow_forward
- how and why the stagnation enthalpy is defined? How does it differ from ordinary static enthalpyarrow_forwardA stream of air at 77°F and 1.2 atm absolute flowing at a rate of 225 ft3/h is blown through ducts that pass through the interior of a large industrial motor. The air emerges at 500°F. Calculate the rate atwhich the air is removing heat generated by the motor. What assumption have you made about the pressure dependence of the specific enthalpy of air?arrow_forwardAn ideal gas enters a turbine with a velocity of 40 m/s through an inlet pipe with a diameter of 160 mm. The ideal gas enters the turbine at a temperature of 660°C and a pressure of 800 kPa. The ideal gas leaves the turbine with a velocity of 150 m/s through an outlet pipe with a diameter of 100 mm. The power output from the turbine is 350 kW. The heat lost from the turbine to the surrounding amounts to 6% of the power output from the turbine. Changes in kinetic energy and potential energy can be neglected. For the ideal gas, use R = 0.287 kJ/kg.K and c, = 1.11 kJ/kg.K| i) Sketch the system/control volume for the above problem Show the boundary/control surface and energy interactions clearly in the sketch. 11) Determine the mass flow rate of the ideal gas, kg/s. i11) Determine the temperature of the ideal gas leaving the turbine, °C. iv) Determine the pressure of the ideal gas leaving the turbine, kPa. v) Suggest one way to increase the power output from the turbine.arrow_forward
- Air enters a converging–diverging nozzle with low velocity at 2.4 MPa and 120°C. If the exit area of the nozzle is 3.5 times the throat area, what must the back pressure be to produce a normal shock at the exit plane of the nozzle?arrow_forward(c) An ideal gas enters a turbine with a velocity of 40 m/s through an inlet pipe with a diameter of 160 mm. The ideal gas leaves the turbine at a temperature of 527°C and a pressure of 500 kPa. The ideal gas leaves the turbine with a velocity of 150 m/s through an outlet pipe with a diameter of 100 mm. The power output from the turbine is 350 kW. The heat lost from the turbine to the surrounding amounts to 6% of the power output from the turbine. Changes in kinetic energy and potential energy can be neglected. For the ideal gas, use R = 0.287 kJ/kg.K and c, = 1.11 kJ/kg.K. i) Sketch the system/control volume for the above problem. Show the boundary/control surface and energy interactions clearly in the sketch. ii) Determine the mass flow rate of the ideal gas, kg/s. iii) Determine the temperature of the ideal gas entering the turbine, °C. iv) Determine the pressure of the ideal gas entering the turbine, kPa. v) Suggest one way to increase the power output from the turbine.arrow_forwardA converging–diverging nozzle receives air from a tank at 100 psia and 600°R. The pressure is 28.0 psia immediately preceding a plane shock that is located in the di- verging section. The Mach number at the exit is 0.5 and the flow rate is 10 lbm/sec. Determine: (a) The throat area. (b) The area at which the shock is located. (c) The outlet pressure required to operate the nozzle in the manner described above. (d) The outlet area. (e) The design Mach number.arrow_forward
arrow_back_ios
SEE MORE QUESTIONS
arrow_forward_ios
Recommended textbooks for you
- Elements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
- Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY
Elements Of Electromagnetics
Mechanical Engineering
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Oxford University Press
Mechanics of Materials (10th Edition)
Mechanical Engineering
ISBN:9780134319650
Author:Russell C. Hibbeler
Publisher:PEARSON
Thermodynamics: An Engineering Approach
Mechanical Engineering
ISBN:9781259822674
Author:Yunus A. Cengel Dr., Michael A. Boles
Publisher:McGraw-Hill Education
Control Systems Engineering
Mechanical Engineering
ISBN:9781118170519
Author:Norman S. Nise
Publisher:WILEY
Mechanics of Materials (MindTap Course List)
Mechanical Engineering
ISBN:9781337093347
Author:Barry J. Goodno, James M. Gere
Publisher:Cengage Learning
Engineering Mechanics: Statics
Mechanical Engineering
ISBN:9781118807330
Author:James L. Meriam, L. G. Kraige, J. N. Bolton
Publisher:WILEY
Intro to Compressible Flows — Lesson 1; Author: Ansys Learning;https://www.youtube.com/watch?v=OgR6j8TzA5Y;License: Standard Youtube License