List of top Aeronautical and Aerospace Engineering Questions asked in GATE Aerospace Engineering

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).

In a fluid flow, Mach number is an estimate of _________.

Consider a pair of point vortices with clockwise circulation \( \Gamma \) each. The distance between their centers is \( a \), as shown in the figure. Assume two-dimensional, incompressible, inviscid flow. Which one of the following options is correct?


 

For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length from the leading edge, is _________.

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 \( x \), \[ \frac{\delta}{x} \propto \_\_\_\_\_\_. \]
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).
\( \delta Q \) and \( \delta W \) are the heat and work interactions of a system with its surroundings, and \( dU \) is the change in the internal energy of the system. For an adiabatic process in a closed, constant pressure combustor, which one of the following options is correct?
A general aviation airplane is in steady and level flight. The airplane is prone to adverse yaw. Which one of the following options best describes the deflections of aileron and rudder to achieve a coordinated right turn?
Consider a pair of point vortices with clockwise circulation \( \Gamma \) each. The distance between their centers is \( a \), as shown in the figure. Assume two-dimensional, incompressible, inviscid flow. Which one of the following options is correct?
\includegraphics[width=0.5\linewidth]{20.png}
In a fluid flow, Mach number is an estimate of \_\_\_\_\_.
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 \( x \), \[ \frac{\delta}{x} \propto \_\_\_\_\_\_. \]
For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length from the leading edge, is \_\_\_\_\_\_.
A positively cambered airfoil is placed in a uniform flow (velocity, \( U_\infty \)) at its zero-lift angle of attack. \( M \) is the corresponding pitching moment. Which one of the following representations accurately describes this scenario?
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).
\( \delta Q \) and \( \delta W \) are the heat and work interactions of a system with its surroundings, and \( dU \) is the change in the internal energy of the system. For an adiabatic process in a closed, constant pressure combustor, which one of the following options is correct?
In a fluid flow, Mach number is an estimate of \_\_\_\_\_.
A positively cambered airfoil is placed in a uniform flow (velocity, \( U_\infty \)) at its zero-lift angle of attack. \( M \) is the corresponding pitching moment. Which one of the following representations accurately describes this scenario?
A general aviation airplane is in steady and level flight. The airplane is prone to adverse yaw. Which one of the following options best describes the deflections of aileron and rudder to achieve a coordinated right turn?
Consider a pair of point vortices with clockwise circulation \( \Gamma \) each. The distance between their centers is \( a \), as shown in the figure. Assume two-dimensional, incompressible, inviscid flow. Which one of the following options is correct?
\includegraphics[width=0.5\linewidth]{20.png}
For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length from the leading edge, is \_\_\_\_\_\_.
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 \( x \), \[ \frac{\delta}{x} \propto \_\_\_\_\_\_. \]
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).
\( \delta Q \) and \( \delta W \) are the heat and work interactions of a system with its surroundings, and \( dU \) is the change in the internal energy of the system. For an adiabatic process in a closed, constant pressure combustor, which one of the following options is correct?
\( \delta Q \) and \( \delta W \) are the heat and work interactions of a system with its surroundings, and \( dU \) is the change in the internal energy of the system. For an adiabatic process in a closed, constant pressure combustor, which one of the following options is correct?
A positively cambered airfoil is placed in a uniform flow (velocity, \( U_\infty \)) at its zero-lift angle of attack. \( M \) is the corresponding pitching moment. Which one of the following representations accurately describes this scenario?