Fluids- stagnation pressure

  • Thread starter 4growler
  • Start date
1. The problem statement, all variables and given/known data
When an airplane is flying 200mph at 5000-ft altitude in a standard atmosphere, the air velocity at a certain point on the wing is 273 mph relative to the airplane. What suction pressure is developed on the wing at that point? What is the pressure at the leading edge ( a stagnation point) of the wing???
The pressure of air at this altitude is 12.228 lb/in^2 and the density of air at this altitude is .00238 slugs/ft^3

2. Relevant equations
p(stag) = p(static) + 1/2 rho (vel) ^2

3. The attempt at a solution I have tried different routes and got wrong answers. The answers are -76.0 lb/ft^2 and 88.0 lb/ft^2. I guess I don't know what the question is asking for, I thought it was looking for the difference in the pressure between the plane and the wing.....please help

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