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 122P
To determine
Temperature, pressure and Mach number at a location, where the flow area has area has been reduced by
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solutionStudents have asked these similar questions
How is the Mach number of a flow defined? What does a Mach number of 2 indicate?
1. Air is flowing isentropically through a
converging duct which is fed from a large
reservoir
where
the temperature
and
pressure
are
350
K
and
250
КРа,
respectively. At a certain point along the
duct, where the cross-sectional area is
0.005 m,
Determine the Mach number, temperature
the
pressure
is
150
kPa.
and velocity at that point and also calculate
the mass flow rate. (Ans: 330.1 K, 0.549,
162.8 kPa, 1.718 kg-s).
2. Air is supplied to a converging nozzle from a
large reservoir where the temperature and
pressure are 400 K and 100 kPa, respectively.
At a certain cross-section, the temperature
and pressure are measured to be 383.8 K and
63 kPa, respectively. Assuming isentropic
flow, find the Mach number at this cross-
section and the mass flow rate per unit area.
(Ans: 0.46, 103.3 kg-s1-m?).
3. A converging nozzle is fed with air from a
large reservoir where the temperature and
pressure are 400 K and 170 kPa, respectively.
The nozzle has an exit cross-sectional area of
0.001 m? and…
For steady isentropic flow of perfect gas
in constant area duct, the change of gas
velocity to the sound speed relation can
be given by
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
- The isentropic relation between different properties of flow can be written as:(in picture) By using the given equation and the isentropic flow relations, derivethe equations for the ratio of temperature, pressure,and densityin terms of Mach number.arrow_forwardAir is flowing in a wind tunnel at 12°C and 66 kPa at a velocity of 190 m/s. The Mach number of the flow is (a) 0.56 m/s (b) 0.65 m/s (c) 0.73 m/s (d ) 0.87 m/s (e) 1.7 m/sarrow_forwardRead the question carefully and give me right solution according to the question. If you don't know the solution please leave it. In the piping system assume the air enters the duct at Ma1 = 0.4. The average friction factor for the duct is estimated to be 0.021. If the Mach number at the duct exit is 0.8, and the temperature of cooling the slurry should be >40°C at the duct exit. Determine the length and exit temperature of the duct and if these parameters are suitable for this application.arrow_forward
- 1. Air is flowing isentropically through a converging duct which is fed from a large where the temperature and КРа, respectively. At a certain point along the duct, where the cross-sectional area is reservoir pressure are 350 K and 250 0.005 m?, pressure is 150 kPa. Determine the Mach number, temperature and velocity at that point and also calculate the mass flow rate. (Ans: 330.1 K, 0.549, 162.8 kPa, 1.718 kg-s*).arrow_forwardIs it possible to accelerate a gas to a supersonic velocity in a converging nozzle? Explainarrow_forwardCalculate the Stagnation temperature for steam flowing at 0.1MPa, 350 degC and 480 m/s. Calculate the stagnation pressurearrow_forward
- Does the Mach number of a gas flowing at a constant velocity remain constant? Explain.arrow_forwardThe specific heat ratio of gas is 1.4 .gas is entering through an adibatic nozzle at 800°c and 900 kpa. Exit pressure is found to as 85kpa. The lowest temperature of the gas at exit nozzle?arrow_forwardstagi 900 kPa 1- Air enters a compressor for a mass flow rate of 0.04 kg/s. at a stagnation temperature 358 K. Assuming the AIR compression process to be isentropic, determine the power 0.04 kg/s require. 100 kPa stagnationarrow_forward
- OB Ahydraulic reaction turbine working under a head of 16 m develops 640 kW of power. What is the unit power of the turbine? (a) 10 kW (c) 60 kW (b) 40 kW (d) 160 kWarrow_forwardAir at a total pressure and temperature of 8 atm and 450 K enters a frictionless constant cross-section duct. A heat addition of 850 kJ/kg makes the flow to choke at the duct exit, determine the inlet Mach number and the total pressure and total temperature at the exit.arrow_forwardPls.answer thank you! A cooling tower is used to cool a jacket water loss from the engine. The heat generated by fuel is 2500 KW and cooling loss is 30%. If temperature range of the tower is 15°C. Determine the mass flow of water entering the towerarrow_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