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 20P
An object traveling in atmospheric air emits two pressure waves at different times. At an instant in time, the waves appear as in the figure. Determine the velocity and Mach number of the object and its current location.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solution
Students have asked these similar questions
I need the answer as soon as possible
2-A particle is moving in air at sea level
where the temperature is 15°c. The two
disturbance spheres created by the
particle at points A and B are shown
in the figure below. Determine the
Mach number and the velocity of particle.
6m
3m
B
A
particle
Suppose that a continuous acoustical disturbance is emitted from a source moving at Mach number=2.5 in the atmosphere at an elevation of 500 m above the earth's surface. Determine the time past for an observer on the ground to hear the disturbance from the instant when it was directly overhead, neglect changing in c from ground to the path of airplane assuming standard atmosphere, if:
1-Fixed observer
2- Observer moving in the same direction at a speed of=0.5*c
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
What is the difference between the names defined in an ML let construct from the variables declared in a C bloc...
Concepts Of Programming Languages
ICA 17-24
The decay of a radioactive isotope can be theoretically modeled with the following equation, where C0...
Thinking Like an Engineer: An Active Learning Approach (4th Edition)
A contractor uses a blueprint to build a set of identical houses. Are classes analogous to the blueprint or the...
Starting Out with Java: From Control Structures through Objects (7th Edition) (What's New in Computer Science)
What is a ToolTip?
Starting Out With Visual Basic (8th Edition)
Fill in the blanks in each of the following statements: A relation that has no partial functional dependencies ...
Modern Database Management
List in chronological order the major events that take place when a process is interrupted.
Computer Science: An Overview (13th 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
- I need the answer as soon as possiblearrow_forwardAir enters a diffuser shown in below figure with a speed of 200 m/s. Determine (a) the speed of sound and (b) the Mach number at the diffuser inlet when the air temperature is 30°C. Air Diffuser V = 200 m/s T = 30°Carrow_forwardA moving point disturbance travels at a supersonic speed. It creates two spheres one at time (t) and the next one after (8t) time interval, 36 m ahead. Assuming the medium to be standard sea level atmosphere with 20°C, calculate the Mach number and velocity of the object and the Mach angle of the cone created by the disturbance. V It =3m 36m R=12m i+ Starrow_forward
- Calculate the Mach number of the exit if the diverging duct has an inlet area and velocity of air of 0.5m^2 and 60 m/s respectively. The exit area is 8 times the inlet, and the temperature on the exit is standard atmospheric value. Your answerarrow_forwardThe shock wave photograph of a wedge structure is given. By using this photograph determine the Mach number.arrow_forwardAn aircraft is flying at 440 km/hr at 3 km on a standard day. What is the aircraft Mach Number?arrow_forward
- determine the Mach number, total pressure, and total temperature after the heat interaction for the following gases: a) y= 1.4 and cp 0.24 Btu/(lbm- °R) b) y= 1.325 and cp = 0.28 Btu/(1bm · °R) %3Darrow_forward2. A particle is moving in air at sea level where the temperature is 18°C. The two disturbance spheres created by the particle at points A and B are shown in the figure below. Determine the Mach no. and velocity of the particle. (Hint: For different time intervals choose the first sphere i.e. the bigger) Ans: 0.5, 171 m-s?. 9m 3m Particle <arrow_forwardAt a given instant of time, two pressure waves, each moving at the speed of sound, emitted by a point source moving with constant velocity in a fluid at rest, are shown in the figure below. Determine (a) the Mach number involved, (b) the instantaneous location, I, of the point source. Assumer₁ = 8 in., r₂ = 3 in., /₁ = 3 in. (a) Ma (b) Vt= in.arrow_forward
- Consider a point in an airflow where the local Mach number, static pressure, and static temperature are 2.5, 0.3 atm, and 180 K, respectively. Calculate the local values of P0, T0, T ∗, a∗, and M∗ at this pointarrow_forwardA supersonic aircraft flies at an altitude of 3000 m. An observer on the ground hears noise generated by the aircraft, which is 3000 m away horizontally, after 12 s. assume that the atmosphere is isothermal. Determine: (a) The Mach number of the aircraft. (b) The velocity of aircraft. (c) The distance traveled before the observer hears the noise, and (d) The temperature of the isothermal atmosphere.arrow_forwardAir is flowing in the converging-diverging nozzle shown in the figure below. A = 15 cm² A₁ = 10 cm² Determine the three critical pressure ratios. "pc1= i "pc2= i *pc3 = Shock i A = 25 cm² Determine the Mach number immediately upstream from the shock. Ma₁ = i Determine the Mach number immediately downstream from the shock. Ma₂ iarrow_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