Air is drawn into a small open-circuit wing tunnel as shown in Fig. P3.80. Atmospheric pressure is 98.7 kPa (abs) and the temperature is 27 °C. If viscous effects are negligible, determine the...

Air is drawn into a small open-circuit wing tunnel as

shown in Fig. P3.80. Atmospheric pressure is 98.7 kPa (abs)

and the temperature is 27 °C. 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 50 m/s.