Airplanes typically have a Pitot-static probe located on the underside that measures relative wind speed as the airplane flies.
1 answer:
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Answer:
≅ 111 KN
Explanation:
Given that;
A medium-sized jet has a 3.8-mm-diameter i.e diameter (d) = 3.8
mass = 85,000 kg
drag co-efficient (C) = 0.37
(velocity (v)= 230 m/s
density (ρ) = 1.0 kg/m³
To calculate the thrust; we need to determine the relation of the drag force; which is given as:
=
× CρAv²
where;
ρ = density of air wind.
C = drag co-efficient
A = Area of the jet
v = velocity of the jet
From the question, we can deduce that the jet is in motion with a constant speed; as such: the net force acting on the jet in the air = 0
SO,
We can as well say:
We can now replace in the above equation.
Therefore, =
× CρAv²
The A which stands as the area of the jet is given by the formula:
We can now have a new equation after substituting our A into the previous equation as:
=
× Cρ
Substituting our data from above; we have:
=
×
=
= 110,990N
in N (newton) to KN (kilo-newton) will be:
=
= 110.990 KN
≅ 111 KN
In conclusion, the jet engine needed to provide 111 KN thrust in order to cruise at 230 m/s at an altitude where the air density is 1.0 kg/m³.
Answer: Attached below is the missing diagram
answer :
A) 1) Wr > WI, 2) Qc' > Qc
B) 1) QH' > QH, 2) Qc' > Qc
Explanation:
л = w / QH = 1 - Qc / QH and QH = w + Qc
<u>A) each cycle receives same amount of energy by heat transfer</u>
<u>(</u> Given that ; Л1 = 1/3 ЛR )
<em>1) develops greater bet work </em>
WR develops greater work ( i.e. Wr > WI )
<em>2) discharges greater energy by heat transfer</em>
Qc' > Qc
solution attached below
<u>B) If Each cycle develops the same net work </u>
<em>1) Receives greater net energy by heat transfer from hot reservoir</em>
QH' > QH ( solution is attached below )
<em>2) discharges greater energy by heat transfer to the cold reservoir</em>
Qc' > Qc
solution attached below
