Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 9, Problem 9.7P
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A pressurized tank of water has a 10-cm-diameter orifice at the bottom, where water discharges to the atmosphere. The water level is
2.5 m above the outlet. The tank air pressure above the water level is 250 kPa (absolute), while the atmospheric pressure is 100 kPa.
Neglecting frictional effects, determine the initial discharge rate of water from the tank. (Round the final answer to three decimal
places.)
-Air
250 kPa
dcm
2.5 m
The initial discharge rate of water from the tank is determined to be 18.683
m³/s.
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A 3-m-high large tank is initially filled with water. The tank water surface is open to the atmosphere, and a sharp-edged 10-cm-diameter
orifice at the bottom drains to the atmosphere through a horizontal 80-m-long pipe. The total irreversible head loss of the system is
determined to be 1.500 m. In order to drain the tank faster, a pump is installed near the tank exit. Determine the pump head input
necessary to establish an average water speed of 6.5 m/s when the tank is full. Disregard the effect of the kinetic energy correction
factors. (Round the final answer to three decimal places.)
Water
3 m
10 cm
80 m
The required useful pump head is 1.200 m.
(30 minutes) Consider a converging-diverging nozzle, which is open to stagnant atmosphere
at the inlet and connected to an infinitely large low-pressure reservoir downstream at the
outlet (see the figure below). The ambient pressure (pa) is 1 bar, the throat cross section area
is 0.1 m². Imagine that the pressure in the low-pressure reservoir (p₁) can be changed to
regulate the flow in the nozzle.
Me
Pa=1 bar
A₁ =0.1 m²
Ae
Pv
Pe
Low pressure reservoir
a) It is known that when p₁
=
0.8 bar, the nozzle is choked and the flow in the converging-
diverging nozzle is subsonic. Find the exit cross-section area (Ae), the static pressure at
the exit (pe) and the Mach number at the exit (Me) for this case.
b) Determine the range of vacuum pressure (pv) for which there is a normal shock wave in
the diverging section of the nozzle.
c) Imagine that a pitot-tube is inserted at the exit of the nozzle. What would be the total
pressure reading when: (1) p₁ = 0.8 bar; (2) p, is adjusted such that the…
Chapter 9 Solutions
Fundamentals of Aerodynamics
Ch. 9 - A slender missile is flying at Mach 1.5 at low...Ch. 9 - Consider an oblique shock wave with a wave angle...Ch. 9 - Equation (8.80) does not hold for an oblique shock...Ch. 9 - Consider an oblique shock wave with a wave angle...Ch. 9 - Consider the flow over a 22.2 half-angle wedge. If...Ch. 9 - Consider a flat plate at an angle of attack a to a...Ch. 9 - A 30.2 half-angle wedge is inserted into a...Ch. 9 - Consider a Mach 4 airflow at a pressure of 1 atm....Ch. 9 - Consider an oblique shock generated at a...Ch. 9 - Consider the supersonic flow over an expansion...
Ch. 9 - A supersonic flow at M1=1.58 and p1=1atm expands...Ch. 9 - A supersonic flow at M1=3,T1=285K, and p1=1atm is...Ch. 9 - Consider an infinitely thin flat plate at an angle...Ch. 9 - Consider a diamond-wedge airfoil such as shown in...Ch. 9 - Consider sonic flow. Calculate the maximum...Ch. 9 - Consider a circular cylinder (oriented with its...Ch. 9 - Consider the supersonic flow over a flat plate at...Ch. 9 - (The purpose of this problem is to calculate a...Ch. 9 - Repeat Problem 9.18, except with =30. Again, we...Ch. 9 - Consider a Mach 3 flow at 1 atm pressure initially...Ch. 9 - The purpose of this problem is to explain what...
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