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
Videos
Textbook Question
Chapter 12, Problem 42P
Air passes through a normal shock in a supersonic wind tunnel. Upstream conditions are M1 = 1.8, T'1 =270K, and p1 = 10.0 kPa absolute. Downstream conditions are M2 = 0.6165, T2 = 413.6 K. and p2 = 36.13 kPa absolute. (Four significant figures are given to minimize round off errors.) Evaluate local isentropic stagnation conditions (a) upstream from, and (b) downstream from, the normal shock. Calculate the change in specific entropy across the shock. Plot static and stagnation state points on a Ts diagram.
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 was formed on the surface of a supersonic aircraft at a velocity of 1,600 m/s into still atmospheric air at standard seal level conditions. Calculate:
a) M₁
b) M₂
c) P₂
d) T₂
e) V₂
Nozzle is assuming steady one-dimensional flow. M = 2.731. This is the the supersonic flow of air through a convergent-divergent nozzle. The stagnation temperature = 300K, stagnation pressure at the inlet = 107500Pa, static pressure at the exit=4400Pa, C1 is a constant = 0.1097 for calculating circular cross-sectional area of a convergent-divergent nozzle: A = C1 + x^2 and x (axial distance from the throat) =1m. γ = 1.4 and R=287. Calculate the mass flow rate of air through the nozzle.
Thank You.
Consider a supersonic flow with M = 2, p = 1 atm, and T = 288 K. This flow isdeflected at a compression corner through 20◦. Calculate M, p, T , p0, and T0 behind the resulting oblique shock wave.
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
Rate of change of combined thermal and flow work.
Introduction to Heat Transfer
What are some of the properties that must be possessed by resistance-welding electrodes?
Degarmo's Materials And Processes In Manufacturing
The largest mass of cylinder F that can be supported and the sag yC.
Engineering Mechanics: Statics
ICA 8-18
You have been working to develop a new fictitious compound in the lab. Determine the amount in units o...
Thinking Like an Engineer: An Active Learning Approach (4th Edition)
What are the four basic types of fusion welds?
DeGarmo's Materials and Processes in Manufacturing
A pipeline transporting crude oil (sg = 0.93 ) at 1200 L/min is made of DN 150 Schedule 80 steel pipe. Pumping ...
Applied Fluid Mechanics (7th 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
- 1. Consider a low-speed subsonic wind tunnel designed with a reservoir cross-sectional area A, = 2 m2 and a test-section cross-sectional area A2 = 0.5 m2. The pressure in the test section is P2 = 1 atm. Assume constant density equal to standard sea level density, calculate the pressure (in kPa) required in the reservoir, P1, necessary to achieve a flow velocity V2: 40 m/s in the test section. a. From item no. 1, calculate the mass flow rate (in kg/s) through the wind tunnel. b. Calculate the Mach number of the vehicle in air. c. Calculate the Mach number of the vehicle in hydrogen.arrow_forwardA 20◦ half-angle wedge is mounted at 0◦ angle of attack in the testsection of a supersonic wind tunnel. When the tunnel is operating, thewave angle from the wedge leading edge is measured to be 41.8◦. Whatis the exit-to-throat area ratio of the tunnel nozzle?arrow_forwardAir enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The throat area is one-half that of the discharge of the divergent section. Assuming the Mach number in the throat is 0.75, what are the values of the following quantities at the throat: pressure(atm), temperature(K), linear velocity(m/s), density(kg/m3), and mass velocity(kg/m2s)? What are the values of p*(in atm), T*(in K), u*(in m/s), and G* (in kg/m2.s) corresponding to reservoir conditions? Write your answers according to order of properties asked.arrow_forward
- Consider a wing mounted in the test-section of a subsonic wind tunnel. The velocity of the airflow is 160 ft/s. If the velocity at a point on the wing is 195 ft/s, what is the pressure coefficient at this point?arrow_forwardAir at V_1 = 800 m/s, p_1 = 100 kPa, and T_1 = 300 K passes through a normal shock. Calculate the velocity V_2, temperature T_2, and pressure p_2 after the shock. What would be the values of T_2 and p_2 if the same velocity change were accomplished isentropically?arrow_forwardAERODYNAMICS 1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle of 40° with the flow direction, is attached to the wedge. If the static pressure and temperature in the freestream are 0.5 Pa and 0°C, determine: a. the deflection angle in degrees b. the pressure ratio c. the Mach number in the downstream regionarrow_forward
- When a pitot-static tube is placed in a supersonic flow, the probe reads P = 190 kPa and P = 150 kPa. If the stagnation temperature is 400 K, estimate the freestream Mach number and velocity.arrow_forwardThe velocity ratio (v1/v2) of an isentropic flow through a supersonic wind tunnel is 0.615. if the mach number at the tunnels entry section is 0.95 find the value of mach number at the exitarrow_forwardAir flows isentropically in a channel. Properties at section1 are V1 = 250 m/s, T1 = 330 K, and p1 = 80 kPa. Atsection 2 downstream, the temperature has dropped to 0°C.Find (a) the pressure, (b) velocity, and (c) Mach number atsection 2.arrow_forward
- Consider an infinitely thin flat plate with a 1 m chord at an angle of attackof 10◦ in a supersonic flow. The pressure and shear stress distributions onthe upper and lower surfaces are given by pu = 4 × 104(x − 1)2 +5.4 × 104, pl = 2 × 104(x − 1)2 + 1.73 × 105, τu = 288x−0.2, andτl = 731x−0.2, respectively, where x is the distance from the leading edgein meters and p and τ are in newtons per square meter. Calculate thenormal and axial forces, the lift and drag, moments about the leadingedge, and moments about the quarter chord, all per unit span. Also,calculate the location of the center of pressure.arrow_forwardIn compressible flow, velocity measurements with a Pitot probe can be grossly in error if relations developed for incompressible flow are used. Therefore, it is essential that compressible flow relations be used when evaluating flow velocity from Pitot probe measurements. Consider supersonic flow of air through a channel. A probe inserted into the flow causes a shock wave to occur upstream of the probe, and it measures the stagnation pressure and temperature to be 620 kPa and 340 K, respectively. If the static pressure upstream is 110 kPa, determine the flow velocity.arrow_forward1. What is the significance of subsonic low-speed wind tunnels?2. Distinguish between Calibrated and True Airspeed.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
Extent of Reaction; Author: LearnChemE;https://www.youtube.com/watch?v=__stMf3OLP4;License: Standard Youtube License