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Elza [17]
3 years ago
10

A Carnot engine has a power output of 150 kW. The engine operates between two reservoirs at 20.0°C and 500°

Physics
2 answers:
Nookie1986 [14]3 years ago
8 0
Efficiency η of a Carnot engine is defined to be: 
<span>η = 1 - Tc / Th = (Th - Tc) / Th </span>
<span>where </span>
<span>Tc is the absolute temperature of the cold reservoir, and </span>
<span>Th is the absolute temperature of the hot reservoir. </span>

<span>In this case, given is η=22% and Th - Tc = 75K </span>
<span>Notice that although temperature difference is given in °C it has same numerical value in Kelvins because magnitude of the degree Celsius is exactly equal to that of the Kelvin (the difference between two scales is only in their starting points). </span>

<span>Th = (Th - Tc) / η </span>
<span>Th = 75 / 0.22 = 341 K (rounded to closest number) </span>
<span>Tc = Th - 75 = 266 K </span>

<span>Lower temperature is Tc = 266 K </span>
<span>Higher temperature is Th = 341 K</span>
rjkz [21]3 years ago
5 0

Answer:

8.8 × 10³³J

Explanation:

efficiency of an engine η  = net work output ÷ heat input = 1 - \frac{T_{c} }{T_{H} }

T_{H} = 500 + 273 =773K

T_{C} = 20 + 273 =293K

n_{c} = 1 - \frac{293}{773}

  =0.62

power output= work output = 150kW

power output per hour = 150 × 1000×3600

                                     =5.4×10⁸J

recall, net work output ÷ heat input = 1 - \frac{T_{c} }{T_{H} }

∴ 0.62= 5.4×10⁸ ÷ heat input

heat input= 5.4×10⁸÷0.62

=8.81×10⁸J

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tigry1 [53]

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The player's height at time t is given by

y=v_it-\dfrac g2t^2

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6 0
3 years ago
For the airfoil and conditions in Problem 2.2, calculate the lift-to-drag ratio. Comment on its magnitude.
raketka [301]

Answer:

L/D= 112

Explanation:

Aerodynamics can be defined as the branch of dynamics which deals with the motion of air, their properties and the interaction between the air and solid bodies.

Aerodynamics law explains how an airplane is able to fly. There are four forces of flight, and they are; lift, weight, thrust and drag. The amount of lift generated by a wing divided by the aerodynamic drag is known as the lift to drag ratio.

Lift increases proportionally to the square of the speed.

The solutions to the question is the file attached to this explanation.

Lift,L= qC(l). S---------------------------(1).

and,

Drag,D = qC(d).S ----------------------(2).

Hence, Lift to drag ratio,L/D= C(l)/C(d).

Therefore, we have to compute various angle of attack.(check attached file)...

Then, (L/D) will then be equal to 112.

8 0
3 years ago
The temperature of a 5.0 kg block increases by 3 degrees C when 2,000 J of thermal energy are added to the block. What is the sp
AlexFokin [52]
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A wave pulse traveling to the right along a thin cord reaches a discontinuity where the rope becomes thicker and heavier. What i
Talja [164]

Answer:

the reflected wave is inverted and the transmitted wave is up

Explanation:

To answer this question we must analyze the physical phenomenon, with an wave reaching a discontinuity, we can analyze it as a shock.

Let's start when the discontinuity is with a fixed, very heavy and rigid obstacle, in this case the reflected wave is inverted, since the contact point cannot move

In the event that it collides with an object that can move, the reflected wave is not inverted, this is because the point can rise, they form a maximum at this point.

In the proposed case the shock is when the thickness changes, in this case we have the above phenomena, a part of the wave is reflected by being inverted and a part of the wave is transmitted without inverting.

The amplitude sum of the amplitudes of the two waves is proportional to the lanería that is distributed between them.

When checking the answers the correct one is the reflected wave is inverted and the transmitted wave is up

8 0
3 years ago
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Answer:

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Explanation:

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