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 9P
Carbon dioxide flows at a speed of 10 m/s in a pipe and then through a nozzle where the velocity is 50 m/s, what is the change in gas temperature between pipe and nozzle? Assume this is an adiabatic flow of a perfect gas.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solutionStudents have asked these similar questions
(4) A water hose connected to a nozzle is used to fill a 10 L container. The internal diameter of the hose is 2 cm and the nozzle exit has an inner diameter of 1.7 cm. It takes 30 s to fill up the container. If the inlet pressure is 2 atm and the nozzle exit is 0.8 m above the hosea. What is the velocity (m/s) of water at the outlet stream and at the inlet stream?b. What is the water pressure (atm) at the outlet stream c. What is the mass flow rate of water (kg/s)?
An incompressible fluid flows through a nozzle at 5 kg/s. What is the final velocity if inlet velocity is 5 m/s, and the area of the exit is half the area of the inlet?
impact of a jet
Draw the relationship of the Fact against the jet velocity Vj
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
9.32 A steel wire is suspended vertically from its upper end. The wire is 400 ft long and has a diameter of
in....
Applied Statics and Strength of Materials (6th Edition)
Three rigid bodies, 2,3, and 4, are connected by four springs as shown in the figure. A horizontal force of 1,0...
Introduction To Finite Element Analysis And Design
the internal loading at point B.
Engineering Mechanics: Statics & Dynamics (14th Edition)
A gas-powered cannon shoots projectiles by introducing nitrogen gas at 20.5 MPa into a cylinder having an insid...
Applied Fluid Mechanics (7th Edition)
The beam supports the distributed load shown. Determine the resultant internal loadings on the cross section at...
Mechanics of Materials (10th Edition)
Air flowing at the rate of 1000 cfm and with a temperature of 80 F is mixed with 600 cfm of air at 30 F. Use Eq...
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
- The diffuser in a jet engine is designed to decrease the kinetic energy of air entering the engine compressor. Clearly define the type of transformation between inlet and outlet. Air enters the inlet at 100 kPa at 20 °C and a velocity of 340 m/s and exits at 350 kPa and Cp ? Calculate the 90 °C. Assume that air is a calorically perfect gas. What is P/c, velocity at the outlet Aout Ain Assume that air is a calorically perfect gas. What is the ratioarrow_forwardThis is a velocity triangle for a turbine or compressor, why would W and V go in opposite directions? As doesn’t W follow the shape of the bladesarrow_forwardAir flows steadily at a pressure of 105 kPa at a speed of 0.1m / s and a temperature of 300K in a duct with a diameter of 10 cm. After a deformation in the duct, the flow is uniformly out of the gap with dimensions of 3cm × 6cm out of the possible state. Act like a complete gas, you can make R = 287J / kg.k Assuming an incompressible flow, calculate the velocity of air out of the gap.arrow_forward
- Hot water at a constant volumetric flow rate of Fh and temperature Th(t) is mixed with cold water at a constant volumetric flow rate of Fc and a constant temperature of Tc. Both streams flow into a bathtub, but because of carelessness, the water is overflowing and keeping the bathtub full of water. The bathtub volume is V, and the heat loss can be ignored. Assuming the water in the bathtub is perfectly mixed and constant density and heat capacity, derive the differential equation relating the temperature in the bathtub, T(t), to the temperature of the hot water, Th(t).arrow_forwardAir enters a nozzle with P1 = 585 kPa, T1 = 195 C, and V1 = 100 m/s. If the air exits to the atmosphere where the pressure is 85 kPa, find exiting velocity, assuming an adiabatic process.arrow_forwardFlow of Liquid in a Pipe and Mass Balance. A hydrocarbon liquid enters a simple flow system shown in Fig. 2.6-1 at an average velocity of 1.282 m/s, where A₁ = 4.33 x 10³ m² and p₁ = 902 kg/m³. The liquid is heated in the process and the exit density is 875 kg/m³. The cross-sectional area at point 2 is 5.26 x 10-3 m². The process is steady state. (a) Calculate the mass flow rate m at the entrance and exit. (b) Calculate the average velocity v in 2 and the mass velocity Gin 1. A₁ :45: process P₁ A₂ P₂arrow_forward
- Air 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_forwardCan I have a picture for the answer? HW1: A gas flows through a horizontal pipe with cross-sectional area of 30 cm². At certain point, gauge pressure is 300 kpa when the temperature is 20 °C. At another point, the cross-sectional area is 15 cm² and the gauge pressure is 250 kpa. If the mass flow rate was 0.15 kg/s, find the velocities at these points? Assume isothermal process and take Patm as 100 kpa.arrow_forward(b) Air flows through a cylindrical duct at a rate of 2.3 kg/s. Friction between air and the duct and friction within air can be neglected. The diameter of the duct is 10cm and the air temperature and pressure at the inlet are T₁ 450 K and P₁ = 200 kPa. If the Mach number at the exit is Ma2 determine the rate of heat transfer and the pressure difference across the duct. The constant pressure specific heat of air is cp = 1.005 kJ/kg-K. The gas constant of air is R = 0.287 kJ/kg-K and assume k = 1.4. -arrow_forward
- A hose fills an 80 L container in 1 min 15 sec. If the hose has an exit diameter of 4 cm, what is the flow exit velocity?arrow_forward(548m/sec, 800m/sec, 32.1 cm2, 60.5cm2) nozzles is 11 kg/sec. Find (a) the throat and exit velocity, (b) 7. steam enters a group of convergent-divergent nozzles at a pressure of 2.2MPA and with a temperature of 260C. Equilibrium expansion through the nozzles to an exit pressure of 0.4MPA. Up to the throat the nozzles the flow can be assumed as frictionless. From throat to exit, however, there is an efficiency of expansion of 85%. The steam flow through the nozzles is 11 kg/sec. Find (a) the throat and exit velocity (h the throat and exit areas.arrow_forwardProblem (6.1) Steam at 1.8 MPa and 275 °C expands through a convergent- divergent nozzle to 0.1 MPa. If there is 10 % loss in energy between the throat and the nozzle exit and the vapor flow rate is 0.5 kg/s, determine the cross- sectional area of the throat and the nozzle exit.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