Answer:
a) attached below
b) 0.0337
c) 2730.206 Ib
d) 2320.338 ft/min
Explanation:
<u>a) Plot of the drag polar for this aircraft </u>
first we will calculate :
Wing area (s) = Wing span (b) * Average chord length(c)
= 53.3 * 6 = 319.8 ft^2
Aspect ratio = b^2 / s = 8.883
K = 1 /
eAR = 1 /
Drag polar ( Cd ) = 0.02 + 0.044 C^2L
attached below is a plot of the drag polar
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Attached below is the detailed solution of the remaining part of the question
Answer:
(a) BP = 11.99 KPa
(b) h = 2 m
Explanation:
(a)
Since, the fluid pressure and blood pressure balance each other. Therefore:
BP = ρgh
where,
BP = Blood Pressure
ρ = density of fluid = 1020 kg/m³
g = acceleration due to gravity = 9.8 m/s²
h = height of fluid = 1.2 m
Therefore,
BP = (1020 kg/m³)(9.8 m/s²)(1.2 m)
<u>BP = 11995.2 Pa = 11.99 KPa</u>
(b)
Again using the equation:
P = ρgh
with data:
P = Gauge Pressure = 20 KPa = 20000 Pa
ρ = density of fluid = 1020 kg/m³
g = acceleration due to gravity = 9.8 m/s²
h = height of fluid = ?
Therefore,
20000 Pa = (1020 kg/m³)(9.8 m/s²)h
<u>h = 2 m</u>
Answer:
The steady-state temperature difference is 2.42 K
Explanation:
Rate of heat transfer = kA∆T/t
Rate of heat transfer = 6 W
k is the heat transfer coefficient = 152 W/m.K
A is the area of the square silicon = width^2 = (7/1000)^2 = 4.9×10^-5 m^2
t is the thickness of the silicon = 3 mm = 3/1000 = 0.003 m
6 = 152×4.9×10^-5×∆T/0.003
∆T = 6×0.003/152×4.9×10^-5 = 2.42 K
Given:
voltage, V = 3600V
step-up voltage, V' = 100000 V
Resistance of line, 
Solution:
To calculate % heat loss in long distance power line:
Power produced by AC generator, P =
W
P = 180000 W = 180 kW
At step-up voltage, V = 100000V or 100 kV
current, I = 
I = 
I = 1.8 A
Power line voltage drop is given by:



Power dissipated in long transmission line 
Power dissipated in long transmission line
= 324 W
% Heat loss in power line, 
% Heat loss in power line, 
