An airplane wing with an average cross sectional area of 10 m^2 experiences a lift force of 5000 N. What is
the difference in air pressure, on the average, between the bottom and top of the wing?
a. 5000 Pa
b. 500 Pa
c. 50 Pa
d. 50000 Pa
e. 10 Pa
b. P=F/A=5000/10=500 Pa
Well, to find the difference in air pressure between the bottom and top of the wing, we need to use the formula P = F/A, where P is the pressure, F is the force, and A is the area.
In this case, the force (F) is 5000 N and the cross-sectional area (A) is 10 m^2.
Plugging the values into the formula, we get P = 5000 N / 10 m^2 = 500 Pa.
So, the correct answer is b. 500 Pa.
But let's not get carried away with the wings here. Remember, birds have wings too, but they never have to worry about air pressure. They just fly around, tweeting, and having a good ol' time. Must be nice...
To calculate the difference in air pressure between the bottom and top of the wing, we can use the formula for pressure:
Pressure = Force / Area
Given that the lift force is 5000 N and the cross-sectional area is 10 m^2, we can plug these values into the formula:
Pressure = 5000 N / 10 m^2 = 500 Pa
Therefore, the difference in air pressure, on average, between the bottom and top of the wing is 500 Pa.
The correct answer is b. 500 Pa.
To answer this question, we need to understand the concept of lift force and the relationship between lift force and the pressure difference on an airplane wing.
The lift force on an airplane wing is generated by the pressure difference between the top and bottom surfaces of the wing. According to Bernoulli's principle, as the air flows over the wing, it travels faster over the curved upper surface and slower along the flatter lower surface. This difference in air speed creates a pressure difference. The higher pressure below the wing pushes the wing upward, creating lift.
The pressure difference between the top and bottom surfaces of the wing can be found using the formula:
Pressure difference = Lift force / Wing area
Given that the lift force is 5000 N and the wing area is 10 m^2, we can calculate the pressure difference as follows:
Pressure difference = 5000 N / 10 m^2 = 500 N/m^2
Therefore, the difference in air pressure, on average, between the bottom and top of the wing is 500 Pa.
So, the correct answer is option b. 500 Pa.