A P - 51 Musta ng (WWII plane) is tested in the large windtunnel at NASA Ames. The plane has a pitot - static probe systemmounted. We want to test the P - 51 at a flight speed of 160 mphand altitude of 40,000 ft. T he wind tunnel’s test section has across - sectional area of 5000 ft 2 and a reservoir area of 100,000ft 2 .
What pressure is needed in the reservoir to drive thisflow?
a. Does Bernoulli’s equation apply here? i. Hint: Whatflow condition is required for Bernoulli’s equation?
b. If 1 60 mph is the true airspeed, what is the staticand stagnation pressure? i. Hint: You are given the flight altitudeas 40,000 ft.
c. W h at reservoir pressure is needed to achieve thistest section velocity and pressure?
