FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
6th Edition
ISBN: 9781265141387
Author: Anderson
Publisher: MCG
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Chapter 8, Problem 8.5P
Consider the isentropic flow through a supersonic nozzle. If the test-section conditions are given by
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In 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.
Consider the isentropic flow through a supersonic nozzle. If thetest-section conditions are given by p = 1 atm, T = 230 K, and M = 2,calculate the reservoir pressure and temperature.
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Chapter 8 Solutions
FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
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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- 2. A gas stream (k=1.33) at 100 kPa and 723°C is passing at Mach number 0.7. Its temperature is measured by a thermometer having a recovery factor 0.75. Calculate the indicated temperature and the bias error of temperature.arrow_forwardIn 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.arrow_forwardA flow of air with Mach number M1 = 2, pressure p1 = 0.7 atm, and temperature 630 degR is turned away from itself through an angle of 26.38 deg. Determine the Mach number, the staticpressure, the static temperature, and the stagnation pressure after the turn (all pressures in atm).Also determine the Mach angles at the beginning and end of the expansion fan.arrow_forward
- The ratio of stagnation temperature at the exit and entry of a combustion chamber is 3.75. If the pressure, temperature and flow Mach number at the exit are 2.5 bar, 1000°C and 0.9 respectively, determine (i) Mach number, pressure and temperature of the gas at entry, (ii) total heat supplied per kg of gas, and (iii) the maximum heat that can be supplied. Take y= 1.4 and C, = 1.2 kJ/kg K. [Ans. M1 = 0.255, p1 1.9 bar, T, = 391.4 K, Q = 1301.7 kJ/kg, Qmax 1315.82 kJ/kg]arrow_forwardQ1: Air enters a converging-diverging nozzle of a supersonic wind tunnel at 1 MPa and 300 K with a low velocity. If a normal shock wave occurs at the exit plane of the nozzle at Ma = 2.4, determine the pressure, temperature, Mach number, velocity, and stagnation pressure after the shock wave.arrow_forwardAir flows through a long, isentropic nozzle. The temperature and pressure at the * reservoir are 1000K and 20 atm, respectively. If the Mach number at the entrance is 0.2, determine the gas velocity at the entrance. 634 m/s 127 m/s 478 m/s 254 m/s For a large centrifugal pump, the required net positive suction head is typically around 5 ft 2 ft 15 ftarrow_forward
- An ideal isentropic nozzle is attached to an infinite reservoir that has stagnation conditions 3 MPa and 2250 K, and a constant specific heat of 1.2. If the nozzle's static exit pressure is 38.871 kPa, what is the exit static temperature? Also determine the nozzle's exit Mach number, stagnation pressure, and stagnation temperature.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_forwardAir is expanded from 200 kPa and 500°K through a throat to an exit Mach number of 2.5. If the desired mass flow is 3 kg/s, calculate the throat area, exit pressure, exit temperature, exit velocity, and the discharge area assuming isentropic flow.arrow_forward
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