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
Chapter 12, Problem 50P
Carbon dioxide discharges from a tank through a convergent nozzle into the atmosphere. If the tank temperature and gage pressure are 38°C and 140 kPa, respectively, what jet temperature, pressure, and velocity can be expected? Barometric pressure is 101.3 kPa.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solutionStudents have asked these similar questions
Air flows at 250 m/s through the pipe. The temperature is 400 K and the
absolute stagnation pressure is 280 kPa. Assume isentropic flow. For air
R = 286.9 J/[kg. K] and k = 1.40. (Figure 1)
Figure
0.3 m
1 of 1
Part A
Determine the pressure within the flow.
Express your answer using three significant figures.
Submit
ΜΑ
Provide Feedback
h
P= 220072.60
Pa
Review your calculations and make sure you round to 3 significant figures in the last step.
No credit lost. Try again.
?
Previous Answers Request Answer
A jet-propelled airliner flies at an altitude of 15,000 m and a velocity of 265 m/s. What is the stagnation
pressure and stagnation temperature of the air entering the engine? If the airliner is stationary on the
ground, the engines are running with the same Mach number flow into the engines, and the air flow to each
engine is 35 kg/s, what is the airflow to each engine at the above flight conditions?
Po =
Pa
To = i
mf =
K
kg/s
Air flows at 180 m/sm/s through the pipe. The temperature is 400 KK and the absolute stagnation pressure is 280 kPakPa. Assume isentropic flow. For air R� = 286.9 J/[kg⋅K]J/[kg⋅K] and k� = 1.40
Determine the pressure within the flow.
Express your answer using three significant figures.
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 moment M which the motor must exert in order to position the uniform slender bar of mass m and le...
Engineering Mechanics: Statics
The difference between the cutting tool and machine tools.
Degarmo's Materials And Processes In Manufacturing
What parts are included in the vehicle chassis?
Automotive Technology: Principles, Diagnosis, And Service (6th Edition) (halderman Automotive Series)
The two identical boards are bolted together to form the beam. Determine the maximum spacing s of the bolts to ...
Mechanics of Materials
Why were the distances between the holes too large?
DeGarmo's Materials and Processes in Manufacturing
Solve Ex. 4-4 assuming that the filter is in location A in Fig. 4-9.
Heating Ventilating and Air Conditioning: Analysis and Design
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
- Suppose an aircraft is flying at standard sea-level at M = 0.8 and using a pitot-static tube for airspeed measurement. Determine the actual difference in total and static pressures as would be measured by the pitot-static system. Compare the speed of the aircraft as determined using the actual pressure difference and incompressible flow versus that knowing the actual Mach number. Use k = 1.4.arrow_forwardWhat is the Mach number of an airflow with a velocity of 2000m/s, at 2,000 ft altitude?arrow_forwardAir at 30 lbf/in2 absolute and 200F flows from a reservoir into a duct. The flow is steady, adiabatic, frictionless. The flow rate is 10lbm/s. What are the cross-sectional area, temperature, pressure, and Mach number at the point in the duct where the velocity is 1,400 ft/s?arrow_forward
- On October 3, 1967, pilot William J. "Pete" Knight set a world record that still stands to this day for the fastest flight by a crewed, powered aircraft by flying the North American Aviation X-15 as fast as Mach 6.7 at an altitude of 102,000 ft above sea level. Mach number is the ratio of an object’s velocity to the local speed of sound. Using the table for atmospheric properties with respect to altitude, calculate the speed of sound at an altitude of 100,000 ft. What must have been the velocity of the X-15?arrow_forwardCarbon dioxide gas initially at 500°F and a pressure of 75 psig flows at a velocity of 3000 ft/s. Calculate the stagnation temperature (°F) and pressure (psig) according to the following conditions: (a) using cp at 500°F (b) assuming cp is a quadratic function of temperature between 500°F and 1500°Farrow_forwardAn air tank with a nozzle, has a pressure of twice the standard sea level pressure and density of 2.45 kg/m³. Outside the converging-diverging nozzle, the pressure corresponds to an altitude of 3km and designed to have a mach number of 1.0 and 1.8 at the throat and exit, respectively. The area at the throat is 0.15 square meters. Calculate: a) the temperature and speed of sound in the tank. b) pressure and density at the throat c) mass flow rate at the exit.arrow_forward
- Air at P1 = 1 MPa, T1 = 600 °C and V1 = 150 m/s enters a converging nozzle. The exit area is A2 = 50 cm2 and the back pressure is P2 = 0.7 MPa. What is the mass flow rate (kg/s) through the nozzle? What the is Mach number at the nozzle exit? What would be the flow rate you calculate if you assumed isothermal flow?arrow_forwardAn aircraft is flying at a speed less than 100 meters per second in sea level. Which of the following statement is true? A. density changes are small and the flow can be regarded as incompressible B. the flow should be regarded as compressible since Mach number is less than 0.3 C. the flow should be regarded as compressible since Mach number is greater than 0.3 D. density changes are small and the flow can be regarded as compressiblearrow_forwardGas flowing through a diverging nozzle has at inlet section a temperature of 20 °C, pressure 120 kN/m? and velocity 300 m/s. At the outlet of the nozzle the velocity has fallen to 100 m/s. Assuming an adiabatic flow, what is the values of outlet pressure, temperature, internal energy and specific enthalpy at outlet section. Take y = 1.333 and Cv= 0.86 kJ/kg K.arrow_forward
- A jet transport is flying at a standard altitude of 30,000 feet with a velocity of 550 miles per hour. What is the Mach number?arrow_forwardAn airplane approaches at an altitude of 10 km flying at 600 km/hr. 1. What would you hear, and when would you hear it, if the plane were "hypersonic", traveling three times the speed of sound, or "Mach 3"? That's approximately the fastest military aircraft in routine service today. note: To have higher speeds in the air takes considerably more energy. For example, after two and half minutes of flight, when the first-stage main engines of the Space X Falcon shut down, it is 80 kilometers high and moving at Mach 10 on its way to Earth orbit. The Mach number depends on the temperature of the air.arrow_forwardAt a given point in a flow field or air, Mach number, velocity, and density are 0.9, 300 mps, and 1.2 kg/m^3, respectively. Calculate at this point the dynamic pressure in kPa.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