Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 10, Problem 10.15P
Return to Problem 9.18. where the average Mach number across the two-dimensional flow in a duct was calculated, and where
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The Mach no. of a fixed geometry inlet at overspeeded for starting mode (Ai= 0.13 m2, At= 0.095 m2
An air tank with a nozzle, has a pressure of twice the standard sea level pressure and
density of 2.45 kg/m³. Outside the converging-diverging nozzle, the pressure corresponds
to an altitude of 3km and designed to have a mach number of 1.0 and 1.8 at the throat
and exit, respectively. The area at the throat is 0.15 square meters.
Calculate:
a) the temperature and speed of sound in the tank.
b) pressure and density at the throat
c) mass flow rate at the exit.
b) In a converging-diverging duct the flow conditions are such that a normal shock is formed at the
exit of the diverging section. Upstream of the shock the flow conditions are as below.
Mach number= '5.198', Pressure= '311886.9' Pa and Temperature= '228.72' K. Obtain the Mach
number, pressure, and temperature at the downstream of the shock. Assume standard air
properties (y=1.4).
Chapter 10 Solutions
Fundamentals of Aerodynamics
Ch. 10 - The reservoir pressure and temperature for a...Ch. 10 - A flow is isentropically expanded to supersonic...Ch. 10 - A Pitot tube inserted at the exit of a supersonic...Ch. 10 - For the nozzle flow given in Problem 10.1, the...Ch. 10 - A closed-form expression for the mass flow through...Ch. 10 - Prob. 10.6PCh. 10 - A convergent-divergent nozzle with an...Ch. 10 - For the flow in Problem 10.7, calculate the mass...Ch. 10 - Consider a convergent-divergent nozzle with an...Ch. 10 - A 20 half-angle wedge is mounted at 0 angle of...
Ch. 10 - The nozzle of a supersonic wind tunnel has an...Ch. 10 - We wish to design a supersonic wind tunnel that...Ch. 10 - Consider a rocket engine burning hydrogen and...Ch. 10 - For supersonic and hypersonic wind tunnels, a...Ch. 10 - Return to Problem 9.18. where the average Mach...Ch. 10 - Return to Problem 9.19, where the average Mach...Ch. 10 - A horizontal flow initially at Mach I flows over a...Ch. 10 - Consider a centered expansion wave where M1=1.0...
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