A single stream tube is selected to characterize the air flow past the wing of an aircraft in flight at an altitude of 20,000 ft at an airspeed of 275 ft/s. The free stream cross-sectional area of the steam tube is 0.07 ft^2. 1) What is the air flow speed in the stream tube at a location near the wing where the cross-sectional area of the stream tube is 0.05 ft^2? What is the static pressure at this location? 2) What is the air flow speed in the stream tube at a location near the wing where the cross-sectional area of the stream tube is 0.04 ft^2? What is the static pressure at this location?