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
Concept explainers
Question
Chapter 12, Problem 120P
To determine
The pressure and temperature at the instant where speed equals the speed of sound. Ratio of area. Assume negligible velocity.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solutionStudents have asked these similar questions
Determine the exit velocity for the carbon dioxide nozzle as shown in figure
Consider a rocket engine burning hydrogen and oxygen. The total massflow of the propellant plus oxidizer into the combustion chamber is287.2 kg/s. The combustion chamber temperature is 3600 K. Assumethat the combustion chamber is a low-velocity reservoir for the rocketengine. If the area of the rocket nozzle throat is 0.2 m2, calculate thecombustion chamber (reservoir) pressure. Assume that the gas that flowsthrough the engine has a ratio of specific heats, γ = 1.2, and a molecularweight of 16.
multi-stage high –pressure steam turbine is supplied with steam at a stagnation pressure of 7 MPa and a stagnation temperature of 5000C. The corresponding specific enthalpy is 3410kJ.kg. The steam exhaust from the turbine at a stagnation pressure of 0.7 MPa abs., the steam having been in a super-heated condition throughout the expansion. It can be assumed that the steam behaves like a perfect gas over the range of the expansion and that ᵞ = 1.3. Given that the turbine flow process has a small-stage efficiency of 0.82, determine (1) the temperature and specific volume at the end of the expansion; (2) the re-heat factor. The specific volume of superheated steam is represented by pv=0.231(h-1943), where “p” is in kPa, v is in m3/kg and “h” is in kJ/kg.
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
- Please show your complete solution. Thank you! Air flows in a steady flow manner through a converging tube. At the inlet the pressure is 690kPaabs and the density is 0.838 kg/cu.m. If air enters with a volume flow of 125 cu.m per min at the rate of 94 m/min and the exit section has a diameter of 350mm, determine a.) the mass flow rate, kg/min b.) the diameter of the entrance section and c.) the exit velocity. Assume that the density is constant.arrow_forwardDisregard the velocity at the entrancearrow_forwardWhat is the main purpose of nozzles? Explain with aid of equationsarrow_forward
- Derive the equation for turbine and nozzle with the help of steady energy equation by stating their assumptions.arrow_forwardAir is stored in a tank of 2 m2 in volume at a pressure of 3 MPa and a temperature of 300 K. The gas is discharged through a converging nozzle with an exit cross-sectional area of 0.0012 m'. For a back pressure of 101 kPa, find the time required ·for the tank pressure to drop to 300 kPa. Assume quasi-steady flow through the nozzle, where the steady !low equations are applicable at each instant of time. Also assume that the temperature of the air in the tank Is constant.arrow_forwardThe large compressed - air tank shown in the figure bellow exhausts from a nozzle at an exit velocity of Ve = 235 m / s. Assuming isentropic flow, compute: a) the exit Mach number. b) the pressure in the tank. (take; k = 1.396, Cp = 917 J / Kg.k and R = 260 J / Kg.k) air at 30 ° C tank conditions remain constant Pate = 101 kPaarrow_forward
- Nitrogen enters a diffuser at 200 m/s with a pressure of 80 kPa and a temperature of -20 C. It leaves with a velocity of 15 m/s at an atmospheric pressure of 95 kPa. If the inlet diameter is 100 mm, the exit temperature is nearestarrow_forwardWhich of the ff are statements made in construction the Bernoulli eq? that the velocity at the inlet is negligible that the pressure at the inlet and outlet must be atmospheric that the flow through the orifice is in the laminar regime that the inlet and outlet are on the same level horizontallyarrow_forwardWhy when you observe at the inlet, the flow is almost uniform from radially pipe wall to center?arrow_forward
- The general energy balance equation for a turbine is: Qnet + Wnet = ΔmH + ΔKE + ΔPE What does it mean when the term ΔmH is negative? Describe what changes occured to the fluid's energy, and where it went.arrow_forwardA malfunctioning jet aircraft has an engine working at 10,000 m and producing an internalstagnation pressure of only 210 kPa and a stagnation temperature of 1500 C. The area of thethroat is 0.05 m² and the exit area is 0.2m². What is the momentum of the air leaving thisengine?arrow_forwardThe environmental conditions of a nozzle are required to provide 100 kPa, 20 C values and R-134a constant flow at 200 m / s. Bowl efficiency can be accepted as 90 percent. What should be the pressure and temperature at the nozzle entrance?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
First Law of Thermodynamics, Basic Introduction - Internal Energy, Heat and Work - Chemistry; Author: The Organic Chemistry Tutor;https://www.youtube.com/watch?v=NyOYW07-L5g;License: Standard youtube license