Loose Leaf for Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259683992
Author: Anderson, John
Publisher: McGraw-Hill Education
expand_more
expand_more
format_list_bulleted
Videos
Textbook Question
Chapter 8, Problem 8.2P
The temperature in the reservoir of a supersonic wind tunnel is
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solution
Students have asked these similar questions
In a wind tunnel air enters with a velocity of 200kmph. The static pressure and temperature of the air at the inlet of the tunnel is 110kPa and 27°C respectively. Determine Mach number, stagnation temperature, stagnation pressure and the stagnation density on a test model installed in the wind tunnel. The size of the tunnel is given as 1m x1m square cross-section. Determine the mass flow rate of the air. For air assume R=287J/kgK ; γ=1.4.
Consider the flow of air through a supersonic nozzle. The reservoir pressure and temperature are 5 atm and 500 K, respectively. If the Mach number at the nozzle exit is 3, calculate the exit pressure, temperature, and density.
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.
Chapter 8 Solutions
Loose Leaf for Fundamentals of Aerodynamics
Ch. 8 - Consider air at a temperature of 230 K. Calculate...Ch. 8 - The temperature in the reservoir of a supersonic...Ch. 8 - At a given point in a flow, T=300K,p=1.2atm, and...Ch. 8 - At a given point in a flow, T=700R,p=1.6atm, and...Ch. 8 - Consider the isentropic flow through a supersonic...Ch. 8 - Consider the isentropic flow over an airfoil. The...Ch. 8 - The flow just upstream of a normal shock wave is...Ch. 8 - The pressure upstream of a normal shock wave is 1...Ch. 8 - The entropy increase across a normal shock wave is...Ch. 8 - The how just upstream of a normal shock wave is...
Ch. 8 - Consider a flow with a pressure and temperature of...Ch. 8 - Consider a flow with a pressure and temperature of...Ch. 8 - Repeat Problems 8.11 and 8.12 using (incorrectly)...Ch. 8 - Derive the Rayleigh Pitot tube formula, Equation...Ch. 8 - On March 16, 1990, an Air Force SR-71 set a new...Ch. 8 - In the test section of a supersonic wind tunnel, a...Ch. 8 - When the Apollo command module returned to earth...Ch. 8 - The stagnation temperature on the Apollo vehicle...Ch. 8 - Prove that the total pressure is constant...
Additional Engineering Textbook Solutions
Find more solutions based on key concepts
3.3 It is known that a vertical force of 200 lb is required to remove the nail at C from the board. As the nail...
Vector Mechanics for Engineers: Statics, 11th Edition
23.23 A highly oxidized and uneven round bar is being turned on a lathe. Would you recommend a small or a large...
Manufacturing Engineering & Technology
Comprehension Check 7-14
The power absorbed by a resistor can be given by P = I2R, where P is power in units of...
Thinking Like an Engineer: An Active Learning Approach (3rd 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
For the beam loading of Figure P334, draw the complete shearing force and bending moment diagrams, and determin...
Machine Elements in Mechanical Design (6th Edition) (What's New in Trades & Technology)
3.3 It is known that a vertical force of 200 lb is required to remove the nail at C from the board. As the nail...
Vector Mechanics for Engineers: Statics
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
- Nitrogen at 700 kPa pressure and 300K temperature enters a convergent divergent nozzle at negligible speed and passes through a normal shock wave at the Mach number of 3. Calculate the pressure, temperature, velocity, Mach number and stop pressure in the flow behind the shock wave. Compare the values you find with the values found with the air passing through the normal shockwave under the same conditions.arrow_forwardThe entropy increase across a normal shock wave is 199.5 J/(kg · K). What is the upstream Mach number?PLease show step by step solns for better understanding thank you!arrow_forwardA subsonic airplane is flying at a 5000-m altitude where the atmospheric conditions are 54 kPa and 256 K. A Pitot static probe measures the difference between the static and stagnation pressures to be 16 kPa. Calculate the speed of the airplane and the flight Mach number.arrow_forward
- Find the expression for the ratio of the stagnation pressure after a shock wave to the static pressure before the shock wave as a function of k and the Mach number upstream of the shock wave Ma1arrow_forwardAn aircraft is flying at 440 km/hr at 3 km on a standard day. What is the aircraft Mach Number?arrow_forwardConsider an airplane flying at a velocity of 250 m/s. Calculate its Mach number if it is flying at a standard altitude of (a) sea level, (b) 5 km, (c) 10 km.arrow_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 shock wave photograph of a wedge structure is given. By using this photograph determine the Mach number.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
- Air flows through a long, isentropic nozzle. The temp. and pressure at the reservoir are 1000 K and 20 atm respectively. If the Mach number at the entrance is 0.2, what is the gas velocity at the entrancearrow_forward(a) Write Area-Velocity relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (b) Write Area-density relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (c) Write Area-Mach relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (d) Plot the variation of density, pressure, temperature, velocity and Mach number for compressible flows through a supersonic Convergent-Divergent nozzle Note: Do NOT derive above relations.arrow_forwardThe velocity ratio(v1/v2)of an isentropic flow through a supersonic wind tunnel is 0.915 ifthe velocity and mach number at the exit are 376.95 m/s and 2.60 respectively find the value of speed of sound at the entrancearrow_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