Consider an airplane wing of area 15 m2. The airflow speed over the top of the wing is 205 m/s, while the speed across the bottom is 160 m/s. Estimate the thickness of the wing.

What is the lift force on the wing at sea level at 0°C? (Use your estimate.) ____ N

To estimate the thickness of the wing, we can make use of the concept of Bernoulli's principle. Bernoulli's principle states that an increase in the speed of a fluid (in this case, air) occurs simultaneously with a decrease in pressure or decrease in the fluid's potential energy.

In this case, the airflow speed over the top of the wing is 205 m/s while the speed across the bottom is 160 m/s. This difference in airflow speed creates a pressure difference, resulting in lift force.

To estimate the wing thickness, we need to calculate the difference in pressure between the top and bottom surface of the wing. Here's how you can do it:

1. Calculate the dynamic pressure (q):

q = 0.5 * ρ * V^2

Where ρ is the density of air and V is the velocity of air.
The density of air at sea level at 0°C is approximately 1.225 kg/m^3.

For the top surface of the wing:
q_top = 0.5 * 1.225 kg/m^3 * (205 m/s)^2

For the bottom surface of the wing:
q_bottom = 0.5 * 1.225 kg/m^3 * (160 m/s)^2

2. Calculate the pressure difference (ΔP):

ΔP = q_top - q_bottom

3. Estimate the wing thickness (T):

T = ΔP / (ρ * g * A)

Where g is the acceleration due to gravity (approximately 9.8 m/s^2) and A is the wing area (15 m^2).

Now, to estimate the lift force on the wing at sea level and 0°C, we need to make use of the Bernoulli's principle. The lift force can be calculated as:

Lift force = ΔP * A

Substitute the calculated pressure difference (ΔP) and wing area (A) into the equation to find the lift force.

Please note that this method provides an estimate and may not take into account other factors like airfoil shape and wing design that can affect the actual lift force.