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Air is drawn into a small open-circuit wind tunnel as shown in Fig. 3. Atmospheric pressure is 120.2 kPa (abs) and the temperature is 27°C. If viscous effects are negligible, determine: (a) The pressure at the stagnation point on the nose of the airplane. (b) 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 75 m/s. Test Inlet nozzle section -Diffuser- Fan 73) Inlet Water Fig. 3- Wind Tunnel

Air is drawn into a small open-circuit wind tunnel as shown in Fig. 3. Atmospheric pressure is 120.2 kPa (abs) and the temperature is 27°C. If viscous effects are negligible, determine: (a) The pressure at the stagnation point on the nose of the airplane. (b) 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 75 m/s. Test Inlet nozzle section -Diffuser- Fan 73) Inlet Water Fig. 3- Wind Tunnel

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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Answer a, b
**Wind Tunnel Experiment** Air is drawn into a small open-circuit wind tunnel as shown in Fig. 3. Atmospheric pressure is 120.2 kPa (abs) and the temperature is 27°C. If viscous effects are negligible, determine: (a) The pressure at the stagnation point on the nose of the airplane. (b) 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 75 m/s. **Figure 3 - Wind Tunnel Diagram** The diagram illustrates the layout of a small open-circuit wind tunnel system. The parts are as follows: - **Inlet**: Air enters the tunnel through the inlet, marked by an arrow labeled "Q" indicating the airflow direction. - **Inlet Nozzle**: This section narrows to channel the airflow efficiently into the test section. - **Test Section**: A narrowed area where experiments take place. It has a static pressure tap connected to a manometer filled with water. - **Diffuser**: A section that widens to slow down the airflow before it exits the tunnel. - **Fan**: Located at the end of the tunnel to draw air through the system, with arrows indicating the direction of air drawn by the fan. Components are interlinked in a streamlined sequence to measure various airflow parameters in controlled environments.
Transcribed Image Text:**Wind Tunnel Experiment** Air is drawn into a small open-circuit wind tunnel as shown in Fig. 3. Atmospheric pressure is 120.2 kPa (abs) and the temperature is 27°C. If viscous effects are negligible, determine: (a) The pressure at the stagnation point on the nose of the airplane. (b) 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 75 m/s. **Figure 3 - Wind Tunnel Diagram** The diagram illustrates the layout of a small open-circuit wind tunnel system. The parts are as follows: - **Inlet**: Air enters the tunnel through the inlet, marked by an arrow labeled "Q" indicating the airflow direction. - **Inlet Nozzle**: This section narrows to channel the airflow efficiently into the test section. - **Test Section**: A narrowed area where experiments take place. It has a static pressure tap connected to a manometer filled with water. - **Diffuser**: A section that widens to slow down the airflow before it exits the tunnel. - **Fan**: Located at the end of the tunnel to draw air through the system, with arrows indicating the direction of air drawn by the fan. Components are interlinked in a streamlined sequence to measure various airflow parameters in controlled environments.
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