Question

An airplane is flying at 350mi/h at 4000 m standard altitude. As is typical, the air velocity relative to the upper surface of the wing, near its maximum thickness, is 26 percent higher than the plane's velocity. Using Bernoulli's equation, calculate the absolute pressure at this point on the wing. Neglect elevation changes and compressibility. (The properties of air at 4000 m are p=61633 Pa,rho=0.8191Kg/m3 )

Answer 1

To calculate the absolute pressure at a point on the wing, we can use Bernoulli's equation. By considering the velocity of the air relative to the upper surface of the wing and the given information about the air density, we can calculate the absolute pressure at this point.

Step-by-step explanation:

Bernoulli's equation relates the pressure, density, and velocity of a fluid flowing in a pipe or over a surface. In this case, we can use Bernoulli's equation to calculate the absolute pressure on the upper surface of the wing.

The equation is given by:

P + (1/2)ρv^2 = constant

Where P is the pressure, ρ is the density of the fluid, and v is the velocity of the fluid.

Given that the air velocity relative to the upper surface of the wing is 26 percent higher than the plane's velocity, we can calculate the velocity of the air at this point:

Velocity of the air = 1.26 * 350 mi/h

Now we can use Bernoulli's equation to find the absolute pressure:

P + (1/2)(0.8191)(1.26*350)^2 = 61633 Pa

Solving this equation will give us the value of P, the absolute pressure at this point on the wing.