Fox And Mcdonald's Introduction To Fluid Mechanics
9th Edition
ISBN: 9781118921876
Author: Pritchard, Philip J.; Leylegian, John C.; Bhaskaran, Rajesh
Publisher: WILEY
expand_more
expand_more
format_list_bulleted
Videos
Textbook Question
Chapter 12, Problem 83P
Air discharges through a convergent-divergent nozzle which is attached to a large reservoir. At a point in the nozzle a normal shock wave is detected across which the absolute pressure jumps from 69 to 207 kPa. Calculate the pressures in the throat of the nozzle and in the reservoir.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solution
Students have asked these similar questions
A normal shock wave is positioned in a divergent portion where the cross-sectional area is 95cm of a
convergent-divergent nozzle. The exit and throat areas of the nozzle are 120cm² and 80cm, respectively.
Determine the static and stagnation pressures on either side of the shock when reservoir pressure is
400kPa.
nozzle with an expansion ratio of 10. The inlet
-
8. Air is flowing in a converging-diverging
stagnation pressure P 7.0 10³ N/m², and the pressure in the exhaust region is 1 atm. A
normal shock wave is standing in the nozzle divergence. Determine the area ratio at which
the normal shock wave occurs. Assume y
= 1.40.
4- 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 approximately
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 displacement at point C. El is constant. Prob. 1487
Mechanics of Materials (10th Edition)
How Old Would You Be on Mercury? The length of a Mercurian year is 88 Earth days. Write a program that requests...
Introduction To Programming Using Visual Basic (11th Edition)
What would the following statement, when used in a Java program, display on the screen? system.out.println(Java...
Java: An Introduction to Problem Solving and Programming (8th Edition)
16. In a simple electric circuit, the current (I) must remain below 40 milliarr.ps (I < 40 mA) and must also sa...
Thinking Like an Engineer: An Active Learning Approach (4th Edition)
The ____________ is always transparent.
Web Development and Design Foundations with HTML5 (8th Edition)
These are symbols or words that perform operations on one or more operands. a. punctuation b. programmer-define...
Starting Out with Java: From Control Structures through Objects (7th Edition) (What's New in Computer Science)
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
- A converging -diverging nozzle with a throat area of 0.0052 m^2 is attached to a very large tank of air in which the pressure is 136 kpa and the temperature is 67 C° the nozzle exhaust to the atmosphere with pressure of 105 kpa if the mass flow rate is 2 kg/s determine the exit area and mach number at the throat . the flow in the nozzle is isentropicarrow_forwardA converging–diverging nozzle with a 4:1 exit-area ratioand p0 = 500 kPa operates in an underexpanded condition as in Fig. The receiver pressureis pa = 10 kPa, which is less than the exit pressure sothat expansion waves form outside the exit. For the givenconditions, what will the Mach number Ma2 and the angleϕ of the edge of the jet be? Assume k = 1.4 as usual.arrow_forwardThe Mach number at the exit is ●●●●●●● 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: 2 Po = 700 kPa To - 530 K A₁ = 5 cm² Pb-350 kPa A₂ = 12.5 cm²arrow_forward
- The flow just upstream of a normal shock wave is given by p1 = corresponds to your assigned altitude, T1 =corresponds to your assigned altitude , and M1 = 2.6. Calculate the following properties just downstream of the shock: p2, T2, ρ2, M2, p0,2, T0,2, and the change in entropy across the shock. Altitude given: 5305marrow_forwardneed correrct and uregentyarrow_forwardAir flowing isentropically through a converging nozzle discharges to the atmosphere at standard sea level conditions. At the section where the absolute pressure is 179 kPa, the temperature is 39˚C and the air speed is 177 m/s. Determine the nozzle throat pressure.arrow_forward
- Mx and My are ..........., 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: 2 Po = 700 kPa To 530 K A, -5 cm² Pb=350 kPa у A₂ = 12.5 cm²arrow_forwardA large tank supplies helium through a converging-diverging nozzle to the atmosphere. Pressure in the tank remains constant at 8.00 MPa (abs) and temperature remains constant at 1000 K. There are no shock waves in the nozzle. The nozzle is designed to discharge at an exit Mach number of 3.5. The exit area of the nozzle is 100 mm². Determine the mass flow rate through the device. For helium: specific heat ratio k = 1.66; ideal gas constant R = 2077 J/kg.K. To = 1000 K Po= 8 MPa (abs) Throat Helium A₁ = 100 mm² Ma₁ = 3.5arrow_forwardThe jet is flying at MM = 1.3, where the absolute air pressure is 75 kPakPa . A shock is formed at the inlet of the engine. Assume isentropic flow within the engine. k� = 1.40 for air. What is the stagnation pressure in this region? Express your answer to three significant figures and include the appropriate units. What is the pressure in this region? Express your answer to three significant figures and include the appropriate units.arrow_forward
- Air 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_forwardNeed step by step explanationarrow_forwardThe converging-diverging nozzle(as shown in the figure given below) expands and accelerates dry air to supersonic speeds at the exit where p2 = 8 kPa and T₂ = 240 K. At the throat, p₁ = 284 kPa, T₁= 665 K, and V₁ = 495 m/s. NOTE: This is a multi-part question. Once an answer is submitted, you will be unable to return to this part. Air- D₁ = 1 cm Kg/s D₂ = 2.5 cm Determine the mass flow for a steady compressible flow of an ideal gas.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 Press
Mechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSON
Thermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEY
Mechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage Learning
Engineering 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