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:
300 Joules
Explanation:
Just use the Work formula:
W = F . D
W = 10 . 30
W = 300 Joules
Because no sunlight can penetrate it
Answer:
Explanation:
As we know that the oil drop experiment tells us the balancing the gravitational force by electrostatic force.
So ,
Electrostatic force = Gravitational force
qE=mg
Here , q is charge , E is electric field , m is mass and g is gravity.
so,
Insert values from question,
or
This is the required value of electric field.
Answer: a = 200 Ω, b = 7.5 mA
Explanation:
Re = 100 + 100 = 200 Ω
I = E/R = 1.5/200 = 0.0075 A
