In a fluid flow, Mach number is an estimate of \_\_\_\_\_.
Show Hint
- \( \sqrt{\frac{{inertia force}}{{viscous force}}} \)
- \( \sqrt{\frac{{inertia force}}{{elastic force}}} \)
- \( \sqrt{\frac{{elastic force}}{{viscous force}}} \)
- \( \sqrt{\frac{{viscous force}}{{inertia force}}} \)
The Correct Option is B
Solution and Explanation
Top GATE AE Aeronautical and Aerospace Engineering Questions
- For a two-dimensional incompressible flow over a flat plate, the laminar boundary layer thickness at a distance \( x \) from the leading edge is \( \delta \). If \( Re_x \) is the Reynolds number defined based on length scale \( x \), \[ \frac{\delta}{x} \propto \_\_\_\_\_\_. \]
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In a fluid flow, Mach number is an estimate of _________.
Top GATE AE Fluid Mechanics Questions
- For a two-dimensional incompressible flow over a flat plate, the laminar boundary layer thickness at a distance \( x \) from the leading edge is \( \delta \). If \( Re_x \) is the Reynolds number defined based on length scale \( x \), \[ \frac{\delta}{x} \propto \_\_\_\_\_\_. \]
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- In a low-speed airplane, a venturimeter with a 1.3:1 area ratio is used for airspeed measurement. The airplane’s maximum speed at sea level is 90 m/s. If the density of air at sea level is 1.225 kg/m³, the maximum pressure difference between the inlet and the throat of the venturimeter is \_\_\_\_ kPa (rounded off to two decimal places).
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