Consider an airplane with a total wing surface of 90 m^2. At a certain speed the difference in air pressure below and above the wings is 4.2% of atmospheric pressure. Find the lift on the airplane.
.042 * 1.1*10^5 N/m^2 * 90 m^2
this is incorrect and I got a 0% on the assignment
To find the lift on the airplane, we need to calculate the difference in air pressure times the wing surface area.
Step 1: Calculate the difference in air pressure.
The difference in air pressure below and above the wings is given as 4.2% of atmospheric pressure. Let's denote atmospheric pressure as P. Therefore, the difference in air pressure is 4.2% of P, which can be written as 0.042 * P.
Step 2: Calculate the lift on the airplane.
The lift on the airplane can be calculated by multiplying the difference in air pressure by the wing surface area. The formula for lift (L) is L = (difference in air pressure) * (wing surface area), which in this case is L = (0.042 * P) * 90 m^2.
Note: The value of atmospheric pressure (P) is typically taken as 101325 Pascal (Pa).
Finally, you can substitute the value of atmospheric pressure and calculate the lift on the airplane.