Answer:
The correct option is A = 1960 N/m²
Explanation:
Given that,
Mass m= 20,000kg
Area A = 100m²
Pressure different between top and bottom
Assume the plane has reached a cruising altitude and is not changing elevation. Then sum the forces in the vertical direction is given as
∑Fy = Wp + FL = 0
where
Wp = is the weight of the plane, and
FL is the lift pushing up on the plane.
Let solve for FL since the mass of the plane is given:
Wp + FL = 0
FL = -Wp
FL = -mg
FL = -20,000× -9.81
FL = 196,200N
FL should be positive since it is opposing the weight of the plane.
Let Equate FL to the pressure differential multiplied by the area of the wings:
FL = (Pb −Pt)⋅A
where Pb and Pt are the static pressures on bottom and top of the wings, respectively
FL = ∆P • A
∆P = FL/A
∆P = 196,200 / 100
∆P = 1962 N/m²
∆P ≈ 1960 N/m²
The pressure difference between the top and bottom surface of each wing when the airplane is in flight at a constant altitude is approximately 1960 N/m². Option A is correct
Answer:
Here we do not have the vector, but I will try to give a kinda general solution to this type of problem.
If the vector is written as (a, b, c) we have that the force in the x-axis is of a Newtons, in the y-axis is of b Newtons, and in the z-axis is of c Newtons.
Then, we can calculate the total magnitude of this force as:
F = √( a^2 + b^2 + c^2)
wich gives us the total magnitude of the force, but not a direction or anything like that, this is just a scalar.
Answer:
.17Hz
Explanation:
The formula for frequency is f= 1/T , where T is the period.
f = 1/6 and 1/6 ≈ .17
They surface at night to eat leaves off the ground.
