A roof-cooling system, which operates by maintaining a thin film of water on the roof surface, may be used to reduce air-conditioning costs or to maintain a cooler environment in nonconditioned buildings. To determine the effectiveness of such a system, con- sider a sheet metal roof for which the solar absorptivity α s is 0.50 and the hemispherical emissivity ◰ is 0.3. Representative conditions correspond to a sur- face convection coefficient h of 20 W/m 2 ⋅ K , a solar irradiation G s of 700 W/m 2 , a sky temperature of − 10 ∘ C , an atmospheric temperature of 30 ∘ C , and a relative humidity of 65%. The roof may be assumed to be well insulated from below. Determine the roof surface temperature without the water film. Assuming the film and roof surface temperatures to be equal, determine the surface temperature with thefilm. The solar absorptivity and the hemispherical emissivity of the film−surface combination are α s = 0.8 and ε = 0.9 , respectively.
A roof-cooling system, which operates by maintaining a thin film of water on the roof surface, may be used to reduce air-conditioning costs or to maintain a cooler environment in nonconditioned buildings. To determine the effectiveness of such a system, con- sider a sheet metal roof for which the solar absorptivity α s is 0.50 and the hemispherical emissivity ◰ is 0.3. Representative conditions correspond to a sur- face convection coefficient h of 20 W/m 2 ⋅ K , a solar irradiation G s of 700 W/m 2 , a sky temperature of − 10 ∘ C , an atmospheric temperature of 30 ∘ C , and a relative humidity of 65%. The roof may be assumed to be well insulated from below. Determine the roof surface temperature without the water film. Assuming the film and roof surface temperatures to be equal, determine the surface temperature with thefilm. The solar absorptivity and the hemispherical emissivity of the film−surface combination are α s = 0.8 and ε = 0.9 , respectively.
A roof-cooling system, which operates by maintaining a thin film of water on the roof surface, may be used to reduce air-conditioning costs or to maintain a cooler environment in nonconditioned buildings. To determine the effectiveness of such a system, con- sider a sheet metal roof for which the solar absorptivity
α
s
is 0.50 and the hemispherical emissivity ◰ is 0.3. Representative conditions correspond to a sur- face convection coefficient
h
of
20 W/m
2
⋅
K
, a solar irradiation
G
s
of
700 W/m
2
, a sky temperature of
−
10
∘
C
, an atmospheric temperature of
30
∘
C
, and a relative humidity of 65%. The roof may be assumed to be well insulated from below. Determine the roof surface temperature without the water film. Assuming the film and roof surface temperatures to be equal, determine the surface temperature with thefilm. The solar absorptivity and the hemispherical emissivity of the film−surface combination are
α
s
=
0.8
and
ε
=
0.9
, respectively.
A composite wall is comprised of two large plates separated by sheets of refractory insulation. In the
installation process, the sheets of thickness L = 50 mm and thermal conductivity k = 0.05 W/mK are separated at
1-m intervals by gaps of width w = 10 mm. The hot and cold plates have temperatures and emissivities of T1 =
400 deg C, emissivity1 = 0.85 and T2 = 35 deg C, emissivity2 = 0.5, respectively. Assume that the plates and
insulation are diffuse-gray surfaces.
%3D
Determine the heat loss by radiation through the gap per unit length of the composite wall (normal
to the page).
Recognizing that the gaps are located on a 1-m spacing, determine what fraction of the total heat
loss through the composite wall is due to transfer by radiation through the insulation gap.
Hot side
Gap
w = 10 mm
A. 47 W/m, 9.2%
T1
= 400°C
B. 47 W/m, 10.2%
L = 50 mm
C. 37 W/m, 10.2%
D. 37 W/m, 9.2%
T2 = 35°C
Cold side
1 m
Insulation, k = 0.05 W/m-K
An astronaut performing an extra-vehicular activity(space walk) shaded from the Sun is wearing a spacesuitthat can be approximated as perfectly white (e = 0) exceptfor a 5 cm × 8 cm patch in the form of the astronaut’snational flag. The patch has emissivity 0.300. The spacesuitunder the patch is 0.500 cm thick, with a thermalconductivity k = 0.0600 W/m °C , and its inner surface isat a temperature of 20.0 °C . What is the temperature of thepatch, and what is the rate of heat loss through it? Assumethe patch is so thin that its outer surface is at the sametemperature as the outer surface of the spacesuit under it.Also assume the temperature of outer space is 0 K. You willget an equation that is very hard to solve in closed form,so you can solve it numerically with a graphing calculator,with software, or even by trial and error with a calculator.
- A furnace can be considered like a long semicylindrical duct of diameter D = 5 m. The base (1)
and the dome (2) of the furnace have emissivity's of 0.5 and 0.9 and are maintained at uniform
temperatures of 305 and 1000 K, respectively.
a- Draw the network of the system.
b- Calculate total resistance.
b- Determine the net rate of radiation heat transfer per unit length from the dome to the base
surface.
Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.