Air is drawn into a small open-circuit wind tunnel as shown in Fig. 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 sec- tion is 50 m/s. Inlet Inlet nozzle Test section 3) Water Diffuser- Fan

Structural Analysis
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ISBN:9781337630931
Author:KASSIMALI, Aslam.
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Chapter2: Loads On Structures
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سنب Fluid mechanics
Q1/
Air is drawn into a small open-circuit
wind tunnel as shown in Fig. 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 sec-
tion is 50 m/s.
Inlet
Test
Inlet nozzle, section
(3)
Water
-Diffuser-
Fan
Transcribed Image Text:Q1/ Air is drawn into a small open-circuit wind tunnel as shown in Fig. 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 sec- tion is 50 m/s. Inlet Test Inlet nozzle, section (3) Water -Diffuser- Fan
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