Answer:
Cc= 12.7 lb.sec/ft
Explanation:
Given that
m = 22 lb
g= 32 ft/s²
x= 4.5 in
1 in = 0.083 ft
x= 0.375 ft
Spring constant ,K
K= 58.66 lb/ft
The damper coefficient for critically damped system
Cc= 12.7 lb.sec/ft
A rigid tank contains 3 kg of water initially at 43.97% quality and at a temperature of 120°C. The water is heated until it reac
hes a pressure of 7 bar. Neglect changes in kinetic and potential energy.
a. At what temperature, in °C, will the water become saturated vapor?
b. Determine the heat transfer, in kJ.
c. The work of the cycle, in kJ
a. At what temperature, in °C, will the water become saturated vapor?
b. Determine the heat transfer, in kJ.
c. The work of the cycle, in kJ
1 answer:
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Answer and Explanation:
The answer is attached below
Answer:
Speed of aircraft ; (V_1) = 83.9 m/s
Explanation:
The height at which aircraft is flying = 3000 m
The differential pressure = 3200 N/m²
From the table i attached, the density of air at 3000 m altitude is; ρ = 0.909 kg/m3
Now, we will solve this question under the assumption that the air flow is steady, incompressible and irrotational with negligible frictional and wind effects.
Thus, let's apply the Bernoulli equation :
P1/ρg + (V_1)²/2g + z1 = P2/ρg + (V_2)²/2g + z2
Now, neglecting head difference due to high altitude i.e ( z1=z2 ) and V2 =0 at stagnation point.
We'll obtain ;
P1/ρg + (V_1)²/2g = P2/ρg
Let's make V_1 the subject;
(V_1)² = 2(P1 - P2)/ρ
(V_1) = √(2(P1 - P2)/ρ)
P1 - P2 is the differential pressure and has a value of 3200 N/m² from the question
Thus,
(V_1) = √(2 x 3200)/0.909)
(V_1) = 83.9 m/s
Answer:
Explanation:
The turbine at steady-state is modelled after the First Law of Thermodynamics:
The specific enthalpies at inlet and outlet are, respectively:
Inlet (Superheated Steam)
Outlet (Liquid-Vapor Mixture)
The power produced by the turbine is: