Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 8, Problem 8.2P
The temperature in the reservoir of a supersonic wind tunnel is
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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.
A uniform supersonic airstream travelling at a Mach number of 9.0 passes over a concave corner, as shown in Figure 4. An
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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.
Chapter 8 Solutions
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...
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- 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.arrow_forwardA P-51 Mustang is traveling at 24000 ft altitude. The inlet air temperature is 5 degrees C. Calculate the speed of sound (in m/s) in the intake port. If the average Mach Number of the intake port is 0.46, what is the speed of the intake airflow?arrow_forwardAn aircraft is flying at 440 km/hr at 3 km on a standard day. What is the aircraft 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_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_forwardThe shock wave photograph of a wedge structure is given. By using this photograph determine the Mach number.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_forwardAir 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_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
- A 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) 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_forwardProblem 3. Air enters a duct with a Mach number of M1 = 2.0, and the temperature and pressure are T = 170 K and pi 0.7 atm, respectively. Heat transfer takes place while the flow proceeds down the duct. A converging section (A2/A3 = 1.45) is attached to the outlet, and the exit Mach number M3 = 1. Assume that the inlet conditions and the exit Mach number remain fixed. Find the amount and direction of heat transfer: (a) If there are no shocks in the system; (b) If there is a normal shock someplace in the duct;arrow_forward
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