Given :
Capacitor , C = 55 μF .
Energy is given by :
.
To Find :
The current through the capacitor.
Solution :
Energy in capacitor is given by :

Now , current i is given by :
![i=C\dfrac{dv}{dt}\\\\i=C\dfrac{d[603.02cos(337t)]}{dt}\\\\i=-55\times 10^{-6}\times 603.03\times 337\times sin(337t)\\\\i=-11.18\ sin(337t)](https://tex.z-dn.net/?f=i%3DC%5Cdfrac%7Bdv%7D%7Bdt%7D%5C%5C%5C%5Ci%3DC%5Cdfrac%7Bd%5B603.02cos%28337t%29%5D%7D%7Bdt%7D%5C%5C%5C%5Ci%3D-55%5Ctimes%2010%5E%7B-6%7D%5Ctimes%20603.03%5Ctimes%20337%5Ctimes%20sin%28337t%29%5C%5C%5C%5Ci%3D-11.18%5C%20sin%28337t%29)
( differentiation of cos x is - sin x )
Therefore , the current through the capacitor is -11.18 sin ( 377t).
Hence , this is the required solution .
Answer:
461.65 KJ/Kg
Explanation:
In this question, we are asked to calculate the values of heat transferred in the process.
Please check attachment for complete solution and step by step explanation
Answer:
Because IC microcomputers are smaller and more versatile than previous control mechanisms, they allow the equipment to respond to a wider range of input and produce a wider range of output. They can also be reprogrammed without having to redesign the control circuitry
Explanation:
Answer:
T = 20.42 N
Explanation:
given data
standard altitude = 30,000 ft
velocity Ca = 500 mph = 0.4 m/s
inlet areas Aa = 7 ft² = 0.65 m²
exit areas Aj = 4.5 ft² = 0.42 m²
velocity at exit Cj = 1600 ft/s = 487.68 m/s
pressure exit
j = 640 lb/ft² = 0.3 bar
solution
we get here thrust of the turbojet that is express as
thrust of the turbojet T = Mg × Cj - Ma × Ca + (
j Aj -
a Ag ) .............1
here Ma = Mg
Ma =
a × Ca Aa = 0.042 kg/s
put value in equation 1 we get
T = 0.042 × (487.68 -0.14) + ( 0.3 × - 0.3 × 0.65 )
T = 20.42 N