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 80P
Testing of a demolition explosion is to be evaluated. Sensors indicate that the shock wave generated at the instant of explosion is 30 MPa absolute. If the explosion occurs in air at 20°C and 101 kPa, find the speed of the shock wave, and the temperature and speed of the air just after the shock passes. As an approximation assume k = 1.4. Why is this an approximation?
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solutionStudents have asked these similar questions
A jet fighter plane travels in horizontal flight at Mach 1.20 (that is, 1.20 times the speed of sound in air). At the instant an observer on the ground hears the shock wave, what is the angle her line of sight makes with the horizontal as she looks at the plane?
A normal shock wave propagates into atmosphere where the atmospheric temperature is equal
336K
and pressure is 0.8 atm. For a given pressure ratio of p2/p₁ 41
to T₁ =
a)
Assuming stationary atmosphere, calculate the shock wave velocity and the velocity induced behind
the shock wave. Also calculate the temperature, total pressure and total temperature of the fluid
particles behind the shock wave using equations for moving normal shock.
=
An 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 compressible
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
The cylinder volume below the constant loaded piston has two compartments, A and B, filled with water, as shown...
Fundamentals Of Thermodynamics
Solar flux of 900W/m2 is incident on the top side of a plate whose surface has a solar absorptivity of 0.9 and ...
Fundamentals of Heat and Mass Transfer
What parts are included in the vehicle chassis?
Automotive Technology: Principles, Diagnosis, and Service (5th Edition)
9.3 Determine the tensile stress in each segment of the bar shown. Segment AB has a square cross section 2 in. ...
Applied Statics and Strength of Materials (6th Edition)
Determine the angular velocity of the radial line OA at this instant.
Engineering Mechanics: Dynamics (14th Edition)
27. A “normal” blood pressure has a gauge pressure of 120 millimeters of mercury [mm Hg] (systolic reading) ove...
Thinking Like an Engineer: An Active Learning Approach (4th Edition)
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
- Calculate the change in Temperature (T2) after a cooled Helium gas with velocity (v1) and speed of sound (va1)of 642.78 m/s and 360.51 m/s, respectively, passed through a normal shock wave. (Round-off using 2 decimal places and do not include the units in your answer)arrow_forwardThe flow just upstream of a normal shock wave is given by p1 = 1 atm,T1 = 288 K, and M1 = 2.6. Calculate the following properties justdownstream of the shock: p2, T2, ρ2, M2, p0,2, T0,2, and the change inentropy across the shock.arrow_forwardConsider a Lear jet flying at a velocity of 250 m/s at an altitude of 10 km,where the density and temperature are 0.414 kg/m3 and 223 K,respectively. Consider also a one-fifth scale model of the Lear jet beingtested in a wind tunnel in the laboratory. The pressure in the test section ofthe wind tunnel is 1 atm = 1.01 × 105 N/m2. Calculate the necessaryvelocity, temperature, and density of the airflow in the wind-tunnel testsection such that the lift and drag coefficients are the same for thewind-tunnel model and the actual airplane in flight.arrow_forward
- At the seashore, you observe a supersonic aircraft moving overhead at an elevation of 2500 m, you hear the plane 5.5 seconds after it passes directly overhead. Using a nominal air temperature of 15°C, estimate the Mach number and speed of the aircraft. T = 15°C Mach cone z = 2500 marrow_forward4. What is the limit of density change across a Normal shock wave in perfect gas. P2_ Y +1 lim M1-00 PI Y - 1arrow_forwardThe driver and driven gases in a shock tube are both air at 300 K. Assume p4/p1 = 8.006. After the diaphragm is broken, an incident shock wave is propagating into the driven section and an incident expansion wave is propagating into the driver section. If the strength of the incident shock (p2/p1) is 2.6, a. Calculate the strength of the incident expansion wave (p3/p4). b. Calculate the induced mass motion velocity behind the expansion wave. c. Find the propagation velocity of the head expansion wave. d. Find the propagation velocity of the tail expansion wave.arrow_forward
- A supersonic aircraft flies with a speed of 2750 km/h at 27 °C and 100 kPa weather conditions. Two oblique shock waves are generated at leading nose and front window edges as shown in Figure (1). The deflection angles of nose and window edges are 15° and 9° respectively. Determine: 1. Mach number upstream the first shock wave (M1) 2. Normal Mach number upstream the first shock wave (Ma1) 3. Normal Mach number downstream the first shock wave (Myı) 4. Mach number upstream the second shock wave (M) 5. Normal Mach number upstream the second shock wave (M2) 6. Normal Mach number downstream the second shock wave (My2) 7. Mach number downstream the second shock wave (M3) 8. The pressure downstream the second shock wave. Take (y=1.4 and R = 287 J/kg.K) for air. Oblique shock waves M3 ? T1=27°C 9° M2 P3 ? P1 =100 kPa HHAUR HANCE 15° 1.22 1.62 0.72 1.45 2.2arrow_forwardA supersonic aircraft flies with a speed of 2750 km/h at 27 °C and 100 kPa weather conditions. Two oblique shock waves are generated at leading nose and front window edges as shown in Figure (1). The deflection angles of nose and window edges are 15° and 9° respectively. Determine: 1. Mach number upstream the first shock wave (M1) 2. Normal Mach number upstream the first shock wave (Ma1) 3. Normal Mach number downstream the first shock wave (My1) 4. Mach number upstream the second shock wave (M2) 5. Normal Mach number upstream the second shock wave (M2) 6. Normal Mach number downstream the second shock wave (My2) 7. Mach number downstream the second shock wave (M3) 8. The pressure downstream the second shock wave. Take (y=1.4 and R = 287 J/kg.K) for air. Oblique shock waves M3 ? T1=27°C 9° M2 P3 ? P1 = 100 kPa AR FRANe 15°arrow_forwardA 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_forward
- A uniform supersonic airstream travelling at a Mach number of 9.0 passes over a concave corner, as shown in Figure 4. An oblique shockwave, which makes an angle of 30° with the flow direction, is attached to the corner under the given conditions. If the pressure and temperature in the uniform flow are 45 kPa and -30 °C respectively, determine the Mach number and deflection angle behind the wave.arrow_forwardAn airplane is flying at a pressure altitude of 15 km with a velocity of 619 m/s. The outside air temperature is 220 K. What is the pressure measured by a Pitot tube mounted on the nose of the airplane?arrow_forward58. Find the height of a supersonic airplane (v = 670 m-s1, T = - 44 C°) when the time between seeing above observer and hearing is 8.8 sec.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
Thermodynamic Availability, What is?; Author: MechanicaLEi;https://www.youtube.com/watch?v=-04oxjgS99w;License: Standard Youtube License