The outer surface of a spacecraft in space has an emissivity of 0.6 and an absorptivity of 0.2 for solar radiation. If solar rad
1 answer:
Answer:
T surface = 3.9°C
Explanation:
given data
emissivity 0.6
absorptivity = 0.2
solar radiation is incident rate = 1200 W/m²
solution
we get here surface temperature by equality of emitted and absorbed heat rate that is
Q (absorbed) = Q (heat ) .................1
α Qinc =
T surface = ..........................2
put here value and we get
T surface =
T surface = 276.9 K
T surface = 3.9°C
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Answer:
a) ∝ and β
The phase compositions are :
C = 5wt% Sn - 95 wt% Pb
C = 98 wt% Sn - 2wt% Pb
b)
The phase is; ∝
The phase compositions is; 82 wt% Sn - 91.8 wt% Pb
Explanation:
a) 15 wt% Sn - 85 wt% Pb at 100⁰C.
The phases are ; ∝ and β
The phase compositions are :
C = 5wt% Sn - 95 wt% Pb
C = 98 wt% Sn - 2wt% Pb
b) 1.25 kg of Sn and 14 kg Pb at 200⁰C
The phase is ; ∝
The phase compositions is; 82 wt% Sn - 91.8 wt% Pb
Csn = 1.25 * 100 / 1.25 + 14 = 8.2 wt%
Cpb = 14 * 100 / 1.25 + 14 = 91.8 wt%
Answer: The exit temperature of the gas in deg C is .
Explanation:
The given data is as follows.
= 1000 J/kg K, R = 500 J/kg K = 0.5 kJ/kg K (as 1 kJ = 1000 J)
= 100 kPa,
We know that for an ideal gas the mass flow rate will be calculated as follows.
or, m =
=
= 10 kg/s
Now, according to the steady flow energy equation:
= 5 K
= 5 K + 300 K
= 305 K
= (305 K - 273 K)
=
Therefore, we can conclude that the exit temperature of the gas in deg C is .