Air is drawn into a small open-circuit wing tunnel as shown. Atmospheric pressure is 98.7 kPa (abs) and the temperature is 45 degrees Celsius. If viscous effects are negligible, determine the pressure at the stagnation point on the nose of the airplane. Also determine the manometer reading, h, for the manometer attached to the static pressure tap within the test section of the wind tunnel if the air velocity within the test section is 60 m/s.