Air is drawn into a small open-circuit wing tunnel as shown in Fig. P3.80. Atmospheric pressure is \(98.7 \mathrm{kPa}\) (abs) and the temperature is \(27^{\circ} \mathrm{C}\). 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 \(50 \mathrm{~m} / \mathrm{s}\).

Figure P3.80

Transcribed Image Text:

Test Inlet nozzle section Diffuser- Inlet -Water Fan!