Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 10, Problem 10.4P
For the nozzle flow given in Problem 10.1, the throat area is
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5. A wind tunnel consists of an entry contraction, a constant-area working section of area
0.5 m?, a diffuser and a fan of area 1 m?, as shown in Fig. 2. The air is pulled from the
atmosphere through the contraction into the working section where its speed is 20 m/s,
and from there it flows through the diffuser into the fan, which returns it to the
atmosphere. Calculate the static and stagnation pressures at:
a. The working section
b. The inlet to the fan
C.
The exit from the fan, assuming no change in air speed across the fan.
d. Calculate the power supplied by the fan to the air.
Fan
V = 20 m/s
Working section
Diffuser
Contraction
Figure 2
2)
flow is exhausted from the nozzle exit at standard sea level conditions with a velocity of 50
m/s, calculate the height difference in a U-tube mercury manometer with one side connected
Consider the nozzle of a subsonic turbojet with contraction ratio of 2:1. If the jet
to the nozzle inlet and the nozzle exit.
as density decreases, mass flow rate:
a. decrese
b. increase
c. stays the same
(provided the diameter of nozzle is constant)
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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