Determine the pressure at stagnation point on the nose

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Reference no: EM13309795

air is drawn into a small a small open-circuit wing tunnel Atmospheric pressure is 98.7 kPa (abs) and the temperature is 27 C. if viscous effects are neglible, determine the pressure at 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

Reference no: EM13309795

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