Fox and McDonald's Introduction to Fluid Mechanics
9th Edition
ISBN: 9781118912652
Author: Philip J. Pritchard, John W. Mitchell
Publisher: WILEY
expand_more
expand_more
format_list_bulleted
Textbook Question
thumb_up100%
Chapter 12, Problem 59P
Air flows isentropically through a converging-diverging nozzle from a large tank containing air at 250°C. At two locations where the area is 1 cm2, the static pressures are 200 kPa and 50 kPa. Find the mass flow rate, the throat area, and the Mach numbers at the two locations.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solutionStudents have asked these similar questions
Air is flowing in a convergent nozzle. At a particular location within the nozzle the pressure is 280 kPa, the stream temperature is 345 K. and the velocity is 150 m/s.
If the cross-sectional area at this location is 9.29 x 103 m², find: (a) The Mach number at this location,
(b) The stagnation temperature and pressure.
(c) The area, pressure, and temperature at the exit where M-1.0. (d) The mass rate of flow for the nozzle.
Indicate any assumptions you may make and the source of data used in the solution.
An air nozzle has an exit area 1.6 times the throat area. If a normal shock occurs at a plane where the area is 1.2 times the throat area, find the pressure,
temperature, and Mach number at the exit. The stagnation temperature and pressure before the shock are 310K and 700KP..
Air flows through a converging-diverging (c-d) nozzle. It is supplied from a large air reservoir in which the temperature is 446 K and the pressure is 190 kPa. The velocity and the cross-sectional area at the nozzle exit are 594 m/s and 0.0005 m^2, respectively. Find the followings:
Mach number at exit is
Area of the throat is
The mass flow rate of air is
The exit temperature is
The exit pressure is
Chapter 12 Solutions
Fox and McDonald's Introduction to Fluid Mechanics
Ch. 12 - Air is expanded in a steady flow process through a...Ch. 12 - Five kilograms of air is cooled in a closed tank...Ch. 12 - Air is contained in a piston-cylinder device. The...Ch. 12 - Calculate the power delivered by the turbine per...Ch. 12 - If hydrogen flows as a perfect gas without...Ch. 12 - A 1-m3 tank contains air at 0.1 MPa absolute and...Ch. 12 - Air enters a turbine in steady flow at 0.5 kg/s...Ch. 12 - Natural gas, with the thermodynamic properties of...Ch. 12 - Carbon dioxide flows at a speed of 10 m/s in a...Ch. 12 - In an isothermal process, 0.1 cubic feet of...
Ch. 12 - Calculate the speed of sound at 20C for (a)...Ch. 12 - An airplane flies at 550 km/hr at 1500 m altitude...Ch. 12 - Actual performance characteristics of the Lockheed...Ch. 12 - For a speed of sound in steel of 4300 m/s,...Ch. 12 - Determine and plot the Mach number of an...Ch. 12 - Investigate the effect of altitude on Mach number...Ch. 12 - The grandstand at the Kennedy Space Center is...Ch. 12 - Use data for specific volume to calculate and plot...Ch. 12 - An object traveling in atmospheric air emits two...Ch. 12 - An object traveling in atmospheric air emits two...Ch. 12 - While at the seashore, you observe an airplane...Ch. 12 - The temperature varies linearly from sea level to...Ch. 12 - Prob. 23PCh. 12 - A photograph of a bullet shows a Mach angle of 32....Ch. 12 - An F-4 aircraft makes a high-speed pass over an...Ch. 12 - All aircraft passes overhead at 3 km altitude. The...Ch. 12 - A supersonic aircraft flies at 3 km altitude at a...Ch. 12 - For the conditions of Problem 12.27, find the...Ch. 12 - The Concorde supersonic transport cruised at M =...Ch. 12 - Plot the percentage discrepancy between the...Ch. 12 - Compute the air density in the undisturbed air and...Ch. 12 - Carbon dioxide flows in a duct at a velocity of 90...Ch. 12 - If nitrogen at 15C is flowing and the stagnation...Ch. 12 - An aircraft cruises at M = 0.65 at 10 km altitude...Ch. 12 - High-speed aircraft use air data computers to...Ch. 12 - A supersonic wind tunnel test section is designed...Ch. 12 - Oxygen flows in a passage at a pressure of 25...Ch. 12 - What is the pressure on the nose of a bullet...Ch. 12 - Prob. 39PCh. 12 - Air flows in an insulated duct. At point the...Ch. 12 - Consider steady, adiabatic flow of air through a...Ch. 12 - Air passes through a normal shock in a supersonic...Ch. 12 - A Boeing 747 cruises at M = 0:87 at an altitude of...Ch. 12 - Space debris impact is a real concern for...Ch. 12 - A CO2 cartridge is used to propel a toy rocket....Ch. 12 - Nitrogen flows from a large tank, through a...Ch. 12 - Air flows from the atmosphere into an evacuated...Ch. 12 - Oxygen discharges from a tank through a convergent...Ch. 12 - The hot gas stream at the turbine inlet of a JT9-D...Ch. 12 - Carbon dioxide discharges from a tank through a...Ch. 12 - Air at 100F and 100 psia in a large tank flows...Ch. 12 - Calculate the required diameter of a convergent...Ch. 12 - Steam flows steadily and isentropically through a...Ch. 12 - Nitrogen flows through a diverging section of duct...Ch. 12 - At a section in a passage, the pressure is 30...Ch. 12 - In a given duct flow M = 2.0; the velocity...Ch. 12 - Air flows isentropically through a converging...Ch. 12 - Five pounds of air per second discharge from a...Ch. 12 - Air flows isentropically through a...Ch. 12 - Air, at an absolute pressure of 60.0 kPa and 27C,...Ch. 12 - Carbon dioxide flows from a tank through a...Ch. 12 - A convergent-divergent nozzle of 50-mm tip...Ch. 12 - Air flows adiabatically through a duct. At the...Ch. 12 - Air flows isentropically through a converging...Ch. 12 - Air flows isentropically through a converging...Ch. 12 - Atmospheric air at 98.5 kPa and 20C is drawn into...Ch. 12 - The exit section of a convergent-divergent nozzle...Ch. 12 - Air flowing isentropically through a converging...Ch. 12 - Air flows from a large tank at p = 650 kPa...Ch. 12 - A converging nozzle is connected to a large tank...Ch. 12 - Air at 0C is contained in a large tank on the...Ch. 12 - A large tank initially is evacuated to 10 kPa...Ch. 12 - Air flows isentropically through a converging...Ch. 12 - Air enters a converging-diverging nozzle at 2 MPa...Ch. 12 - Prob. 75PCh. 12 - A jet transport aircraft, with pressurized cabin,...Ch. 12 - A converging-diverging nozzle, with a throat area...Ch. 12 - Air, at a stagnation pressure of 7.20 MPa absolute...Ch. 12 - A small rocket motor, fueled with hydrogen and...Ch. 12 - Testing of a demolition explosion is to be...Ch. 12 - A total-pressure probe is placed in a supersonic...Ch. 12 - Air flows steadily through a long, insulated...Ch. 12 - Air discharges through a convergent-divergent...Ch. 12 - A normal shock wave exists in an airflow. The...Ch. 12 - Air approaches a normal shock at V1 = 900 m/s, p1...Ch. 12 - Air approaches a normal shock at M1 = 2.5, with...Ch. 12 - Air undergoes a normal shock. Upstream, T1 = 35C,...Ch. 12 - If, through a normal shock wave in air, the...Ch. 12 - The stagnation temperature in an airflow is 149C...Ch. 12 - A supersonic aircraft cruises at M = 2.2 at 12 km...Ch. 12 - The Concorde supersonic transport flew at M = 2.2...
Additional Engineering Textbook Solutions
Find more solutions based on key concepts
Determine the resultant internal normal force, shear force, and bending moment at point C in the beam.
Mechanics of Materials
55. The power required by an airplane is given by P = Fv, where P is the engine power, F is the thrust, and v i...
Thinking Like an Engineer: An Active Learning Approach (4th Edition)
4.12 Calculate the force in each cable for the suspended weight shown.
Applied Statics and Strength of Materials (6th Edition)
What is the purpose of the hole-circle plate on a universal dividing head?
DeGarmo's Materials and Processes in Manufacturing
1.1 What is the difference between an atom and a molecule? A molecule and a crystal?
Manufacturing Engineering & Technology
The 25-kg rectangular access door is held in the 90 open position by the single prop CD. Determine the force F ...
Engineering Mechanics: Statics
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
- 2. An air tank with a nozzle has a pressure of 196.32 KPa and density of 1.9 Kg/m³. Outside the converging- diverging nozzle, the pressure is atmospheric and designed to have a Mach No. of 1.0 and 1.5 at the throat and exit respectively. The area at the throat is 0.11m2. Calculate the following: (a) Temperature and speed of sound at the tank. (b) Pressure, density, temperature and speed of sound at the throat. (c) Mass flow at the exit.arrow_forwardThe velocity ratio(v1/v2)of an isentropic flow through a supersonic wind tunnel is 0.915 ifthe velocity and mach number at the exit are 376.95 m/s and 2.60 respectively find the value of speed of sound at the entrancearrow_forwardAn air nozzle has an exit area 1.6 times the throat area. If a normal shock occurs at a plane where the area is 1.2 times the throat area, find the pressure, temperature, and Mach number at the exit. The stagnation temperature and pressure before the shock are 310 K and 700 kPa, 4.3.arrow_forward
- Air is flowing in a convergent nozzle. The stagnation pressure is 350 KPa , the stagnation temperature is 400 K and Mach number is 0.7. If the cross sectional area at this location is 10 × 10-3 m² , find 1) The static temperature and static pressure 2) The velocity at this location. 3) The area and static temperature and static pressure at the exit where Mach number =1arrow_forwardThe velocity ratio (v1/v2) of an isentropic flow through a supersonic wind tunnel is 0.615. if the mach number at the tunnels entry section is 0.95 find the value of mach number at the exitarrow_forward2. Air flow isentropically through a supersonic convergent divergent nozzle with 0.5 kg/s. At the inlet, the pressure is 680 kPa and the temperature is 295 K, and the area is 6.5 cm?. If the exit area is 13 cm? calculate: a- The stagnation pressure and temperature. b- The exit Mach number. c- The exit pressure and temperature. d- The area and velocity at the throat. e- What will be the corresponding exit Mach number if the flow completely subsonic in the nozzle?arrow_forward
- Q1/2. Air flow isentropically through a supersonic convergent divergent nozzle with 0.6 kg/s. At the inlet, the pressure is 700 kPa and the temperature is 300 K, and the area is 7 cm. If the exit area is 14 cm? calculate: a- The stagnation pressure and temperature. b- The exit Mach number. c- The exit pressure and temperature. d- The area and velocity at the throat. e- What will be the maximum rate of flow and the corresponding exit Mach number if the flow completely subsonic in the nozzle?arrow_forwardAir enters a convergent-divergent nozzle having a throat area of 930 cm? and attains a Mach number of 2.5 at the exit. The supply air is a pressure of 1.05 bar and a temperature of 21 °Cand is having negligible velocity. Find the mass flow rate, area and fluid properties (p, T, pand v) at the exit of the nozzle.arrow_forwardAir enters a convergent-divergent nozzle having a throat area of 930 cm? and attains a Mach number of 2.5 at the exit. The supply air is a pressure of 1.05 bar and a temperature of 21 °C and is having negligible velocity. Find the mass flow rate, area and fluid properties (p, T, pand v) at the exit of the nozzle.arrow_forward
- Q4/ Air enters a duct with a Mach number of 2.0, and the temperature and pressure are 170 K and 0.7 bar, respectively. Heat transfer takes place while the flow proceeds down the duct. A converging section (A2/A3 = 1.45) is attached to the outlet as shown in Fig. Q4, and the exit Mach number is 1.0. Assume that the inlet conditions and exit Mach number remain fixed. Find the amount and direction of heat transfer in the duct: (a) If there are no shocks in the system. (b) If there is a normal shock someplace in the duct. M, - 2.0 T,- 170 K P-0.7 bar M, = 1.0 Fig.Q4 AzlA, = 1.45arrow_forwardAir enters a convergent-divergent nozzle having a throat area of 400 cm? and attains a Mach number of 1.5 at the exit. The supply air is a pressure of 1.05 bar and a temperature of 40°Cand is having negligible velocity. Find the mass flow rate, area and fluid properties (p, T, p and v) at the exit of the nozzle.arrow_forward4- Air at stagnation pressure of 600 kpa and stagnation temperature of 530 K enters a frictionless convergent- divergent nozzle as shown in figure the throat area is 5cm2 and the exit area is 12.5 cm2, the back pressure is 300kpa, and normal shock occurs within the divergent section. Determine the following: A- The Mach number at the exit B- The change in stagnation pressure C- Mx and My are D- The cross sectional area where the shock occurs is approximatelyarrow_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