As I was returning to Colgate from Thanksgiving break, I was
sitting on the plane and began to wonder about the physics of flight,
specifically how much upward pressure is exerted on the wings at take off. To
do this I used the equation: P= F/A. To find the force in this equation I used the following model:
during the plane will accelerate in the positive y-direction (upwards) for the
first 500ft. (152.4m) traveled in the y-direction and travel at a constant
speed in the y-direction as it passes through the 10,000ft. (3,048m) mark on
its way to 28,000ft (8,536.6 m) (the cruising altitude). I will use this model
to solve for the acceleration during the first 152.4m using kinematics. I will
then use the equation F – mg = ma (where F is the upward force and a is the
acceleration just found) to find F. For the area of the plane, the total area
of the underside of the plane I used the area fuselage (modeled after a
rectangle) plus the area of the wings (provided on the informational page for
the plane, a Bombardier CRJ-200). The calculations are as follows:

I estimated the time it took to go from take-off to cruising
altitude to be about 8 min. (or 480 sec).

y = yo +v-y(t)+1/2(a-y)(t^2)

(t = time of acceleration)

since yo and v-y = 0, y = ½(a-y)(t^2)

152.4(2)/(t^2) = a-y

vf = vo + (303.8/(t^2)) t = 303.8/t

(vf is a constant velocity as it passes through the 10,000
ft. mark)

v = y/t

vf = (3048 – 152.4) /
(480 – t)

303.8/t = (3048-152.4) / (480 – t)

t= 45.6s

a-y = .15m/s^2

F – mg = m(a-y)

The maximum take-off weight of the plane is 23,133 Kg

F = (23,133) (9.8 +.15) = 230173.4 N

A = A-fuselage + A-wings

A-fuselage (modeled as a rectangle) = L*W = 26.77*2.69 = 72
m^2

(the length and with of the fuselage are taken from the
plane’s informational page)

A-wings (also on the informational page) = 48.35 m^2

A = 72 + 48.35 =120.35 m^2

P = F/A = 230173.4/120.35 = 1912 Pa

Plane’s informational page - https://www2.bombardier.com/Used_Aircraft/pdf/CRJ200_EN.pdf

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