Atmospheric air enters a 1 0 − m -long. 15 0 − mm -diameter uninsulated heating duct at 6 0 ° C and 0.0 4 kg / s . The duct surface temperature is approximately constant at T s = 15 °C. (a) What are the outlet air temperature, the heat rate q . and pressure drop Δ p for these conditions? (b) To illustrate the tradeoff between heat transfer rate and pressure drop considerations, calculate q and Δ p for diameters in the range from 0.1 to 0.2 m. In your analysis, maintain the total surface area, A s = π D L , at the value computed for pan (a). Plot q. p. and L as a function of the duct diameter.
Atmospheric air enters a 1 0 − m -long. 15 0 − mm -diameter uninsulated heating duct at 6 0 ° C and 0.0 4 kg / s . The duct surface temperature is approximately constant at T s = 15 °C. (a) What are the outlet air temperature, the heat rate q . and pressure drop Δ p for these conditions? (b) To illustrate the tradeoff between heat transfer rate and pressure drop considerations, calculate q and Δ p for diameters in the range from 0.1 to 0.2 m. In your analysis, maintain the total surface area, A s = π D L , at the value computed for pan (a). Plot q. p. and L as a function of the duct diameter.
Solution Summary: The author calculates Remold's number for the type of flow as follows: Mass flow rate is stackreldotm,i=60°C.
Atmospheric air enters a
1
0
−
m
-long.
15
0
−
mm
-diameter uninsulated heating duct at
6
0
°
C
and
0.0
4 kg
/
s
. The duct surface temperature is approximately constant at
T
s
=
15
°C.
(a) What are the outlet air temperature, the heat rate q. and pressure drop
Δ
p
for these conditions?
(b) To illustrate the tradeoff between heat transfer rate and pressure drop considerations, calculate q and
Δ
p
for diameters in the range from 0.1 to 0.2 m. In your analysis, maintain the total surface area,
A
s
=
π
D
L
, at the value computed for pan (a). Plot q. p. and L as a function of the duct diameter.
You are working as an engineer in a bearing systems design company. The flow of
lubricant inside a hydrodynamic bearing (p = 0.001 kg m-1 s-1) can be approximated
as a parallel, steady, two-dimensional, incompressible flow between two parallel plates.
The top plate, representing the moving part of the bearing, travels at a constant speed,
U, while the bottom plate remains stationary (Figure Q1). The plates are separated by
a distance of 2h = 1 cm and are W = 20 cm wide. Their length is L = 10 cm. By
applying the above approximations to the Navier-Stokes equations and assuming that
end effects can be neglected, the horizontal velocity profile can be shown to be
y = +h
I
2h = 1 cm
x1
y = -h
u(y)
1 dP
2μ dx
-y² + Ay + B
moving plate
stationary plate
U
2
I2
L = 10 cm
Figure Q1: Flow in a hydrodynamic bearing. The plates extend a width, W = 20 cm,
into the page.
Question 1
You are working as an engineer in a bearing systems design company. The flow of
lubricant inside a hydrodynamic bearing (µ = 0.001 kg m¯¹ s¯¹) can be approximated
as a parallel, steady, two-dimensional, incompressible flow between two parallel plates.
The top plate, representing the moving part of the bearing, travels at a constant speed,
U, while the bottom plate remains stationary (Figure Q1). The plates are separated by
a distance of 2h = 1 cm and are W = 20 cm wide. Their length is L = 10 cm. By
applying the above approximations to the Navier-Stokes equations and assuming that
end effects can be neglected, the horizontal velocity profile can be shown to be
1 dP
u(y)
=
2μ dx
-y² + Ay + B
y= +h
Ꮖ
2h=1 cm
1
x1
y = −h
moving plate
stationary plate
2
X2
L = 10 cm
Figure Q1: Flow in a hydrodynamic bearing. The plates extend a width, W = 20 cm,
into the page.
(a) By considering the appropriate boundary conditions, show that the constants take
the following forms:
U
U
1 dP
A =…
Question 2
You are an engineer working in the propulsion team for a supersonic civil transport
aircraft driven by a turbojet engine, where you have oversight of the design for the
engine intake and the exhaust nozzle, indicated in Figure Q2a. The turbojet engine can
operate when provided with air flow in the Mach number range, 0.60 to 0.80. You are
asked to analyse a condition where the aircraft is flying at 472 m/s at an altitude of
14,000 m. For all parts of the question, you can assume that the flow path of air through
the engine has a circular cross section.
(a)
← intake
normal
shock
472 m/s
A B
(b)
50 m/s
H
472 m/s
B
engine
altitude: 14,000 m
exhaust nozzle
E
F
exit to
atmosphere
diameter: DE = 0.30 m
E
F
diameter: DF = 0.66 m
Figure Q2: Propulsion system for a supersonic aircraft.
a) When the aircraft is at an altitude of 14,000 m, use the International Standard
Atmosphere in the Module Data Book to state the local air pressure and tempera-
ture. Thus show that the aircraft speed…
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