The oxidized-aluminum wing of an aircraft has a chord length of Lc ◰ 4 m and a spectral, hemispher- ical emissivity characterized by the following distribution. (a)Consider conditions for which the plane is on the ground where the air temperature is 27 ∘ C , the solar irradiation is 800 W/m 2 , and the effective sky temperature is 270 K. If the air is quiescent, what is the temperature of the top surface of the wing? The wing may be approximated as a horizontal, flat plate. (b) When the aircraft is flying at an elevation of approximately 9000 m and a speed of 200 m/s, the air temperature, solar irradiation, and effective sky temperatureare − 40 ∘ C , 1100 W/m 2 and 235K , respectively. What is the temperature of the wing’s top surface? The properties of the air may be approximated as ρ = 0.470 kg/m 3 , μ =1 .50x10 − 5 N ⋅ s / m 2 , K = 0.021 W/m ⋅ K, and Pr =0 .72 .
The oxidized-aluminum wing of an aircraft has a chord length of Lc ◰ 4 m and a spectral, hemispher- ical emissivity characterized by the following distribution. (a)Consider conditions for which the plane is on the ground where the air temperature is 27 ∘ C , the solar irradiation is 800 W/m 2 , and the effective sky temperature is 270 K. If the air is quiescent, what is the temperature of the top surface of the wing? The wing may be approximated as a horizontal, flat plate. (b) When the aircraft is flying at an elevation of approximately 9000 m and a speed of 200 m/s, the air temperature, solar irradiation, and effective sky temperatureare − 40 ∘ C , 1100 W/m 2 and 235K , respectively. What is the temperature of the wing’s top surface? The properties of the air may be approximated as ρ = 0.470 kg/m 3 , μ =1 .50x10 − 5 N ⋅ s / m 2 , K = 0.021 W/m ⋅ K, and Pr =0 .72 .
Solution Summary: The author explains the formula used to calculate the surface temperature of the wing: solar irradiation, air temperature, emissivity, and heat transfer coefficient.
The oxidized-aluminum wing of an aircraft has a chord length of Lc ◰ 4 m and a spectral, hemispher- ical emissivity characterized by the following distribution.
(a)Consider conditions for which the plane is on the ground where the air temperature is
27
∘
C
, the solar irradiation is
800 W/m
2
, and the effective sky temperature is 270 K. If the air is quiescent, what is the temperature of the top surface of the wing? The wing may be approximated as a horizontal, flat plate.
(b) When the aircraft is flying at an elevation of approximately 9000 m and a speed of 200 m/s, the air temperature, solar irradiation, and effective sky temperatureare
−
40
∘
C
,
1100
W/m
2
and 235K
, respectively. What is the temperature of the wing’s top surface? The properties of the air may be approximated as
ρ
=
0.470
kg/m
3
,
μ
=1
.50x10
−
5
N
⋅
s
/
m
2
,
K
=
0.021
W/m
⋅
K, and Pr =0
.72
.
Question #9
A circular ceramic plate that can be modelled as a blackbody is being heated by an electrical
heater. The plate is 30cm in diameter and is situated in a surrounding ambient temperature
of 15°C where the natural convection heat transfer coefficient is 12W/m² K. The efficiency
of the electrical heater to transfer heat to the plate is 80%, the electric power is required
such that the heater needs to keep the surface temperature of the plate at 200°C.
Ambient 15°C Tsurr = 15°C
h = 12 W/m².K
Ceramic plate
-T₂ = 200°C
Welec
(A) Determine the heat emitted from the plate, as a blackbody.
(B) Determine the radiation incident on the plate from the surroundings.
(C) Determine the heat transfer from the plate to the surroundings.
(D) Determine the required electric power.
0.6
0.1
0.3
0.8
none of the choices are correct
A tube carries hot water across a factory in a tube with outer diameter Do = 20 mm. The
tube surface is black, and the surroundings are at 20°C. You may neglect convection during
your analysis.
b) To reduce the rate of heat loss from the pipe, you decide to surround the pipe in a
radiation shield. The shield material you have has inner and outer emissivities of
E2,i = 0.01 and 2,0 = 0.1, respectively. Calculate the rate of heat transfer out of the
tube, per unit length of tube, if the tube surface remains at 450°C and the radiation
shield has a diameter of 60 mm.
Shield, D₂ = 60 mm
2,0
E2,i
Heated tube, D₁₂ = 20 mm
Evacuated
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