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AE 2020
LOWSPEED AERODYNAMICS
Assignment # 2
Please show your work for credit.
Momentum Equation Problems
1) Again, consider steady, compressible flow of air through the turbojet engine shown
below.
The engine is axisymmetric (i.e. it has a circular crosssection) with a radius of
R
=
0
.
4m
.
The aircraft on which this engine is attached is traveling at a speed of
sec
140
1
m
U
=
through standard atmosphere at an altitude of 5 km.
The exhaust velocity varies as a function of the distance from the centerline of the
axisymmetric (i.e. circular crosssection) engine.
The exhaust velocity is given by
u
2
=
u
max
1

r
2
R
2
(
)
where r is the radial coordinate.
The density of the exhaust is
3
2
7
.
0
m
kg
=
ρ
.
Calculate the total force generated by the engine.
Does this correspond to thrust or
to drag?
You must explain your answer for credit.
2) Water flows steadily through a circular pipe around the bend shown in the figure below.
Known conditions are
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 Summer '07
 Ruffin

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