List of top Flight Mechanics Questions asked in GATE AE

A jet-powered airplane is steadily climbing at a rate of 10 m/s. The air density is 0.8 kg/m³, and the thrust force is aligned with the flight path. Using the information provided in the table below, the airplane’s thrust to weight ratio is ___________ (rounded off to one decimal place).

While taking off, the net external force acting on an airplane during the ground roll segment can be assumed to be constant. The airplane starts from rest. $ S_{LO} $ and $ V_{LO} $ are the ground roll distance and the lift-off speed, respectively. $ \alpha V_{LO} $ ($ \alpha>0 $) denotes the airplane speed at 0.5 $ S_{LO} $. Neglecting changes in the airplane mass during the ground roll segment, the value of $ \alpha $ is __________ (rounded off to two decimal places).

While taking off, the net external force acting on an airplane during the ground roll segment can be assumed to be constant. The airplane starts from rest. $ S_{LO} $ and $ V_{LO} $ are the ground roll distance and the lift-off speed, respectively. $ \alpha V_{LO} $ ($ \alpha>0 $) denotes the airplane speed at 0.5 $ S_{LO} $. Neglecting changes in the airplane mass during the ground roll segment, the value of $ \alpha $ is _________ (rounded off to two decimal places).

A jet-powered airplane is steadily climbing at a rate of 10 m/s. The air density is 0.8 kg/m³, and the thrust force is aligned with the flight path. Using the information provided in the table below, the airplane’s thrust to weight ratio is __________ (rounded off to one decimal place).

A general aviation airplane is initially in steady and level flight. The stability coefficient $ \frac{\partial C_m}{\partial q} $ (where $ C_m $ is the airplane pitching moment coefficient and $ q $ is the pitch rate) is negative. The airplane is perturbed with a small nose-up constant pitch rate. Assume that the horizontal tail does not stall during the perturbation, and unsteady effects are neglected. When compared to steady and level flight conditions, which of the following statements is/are true during the perturbed motion?

To achieve longitudinal static stability of a general aviation airplane, which one of the following conditions should be satisfied?

A general aviation airplane is flying at an altitude of 5000 m. The indicated airspeed is 250 km/h. Assume that there are no instrument errors and position errors. Neglecting compressibility effects, which one of the following options is FALSE?

A jet-powered airplane is steadily climbing at a rate of 10 m/s. The air density is 0.8 kg/m³, and the thrust force is aligned with the flight path. Using the information provided in the table below, the airplane’s thrust to weight ratio is \_\_\_\_\_\_ (rounded off to one decimal place).
\includegraphics[width=0.5\linewidth]{52.png}

While taking off, the net external force acting on an airplane during the ground roll segment can be assumed to be constant. The airplane starts from rest. $ S_{LO} $ and $ V_{LO} $ are the ground roll distance and the lift-off speed, respectively. $ \alpha V_{LO} $ ($ \alpha>0 $) denotes the airplane speed at 0.5 $ S_{LO} $. Neglecting changes in the airplane mass during the ground roll segment, the value of $ \alpha $ is \_\_\_\_\_ (rounded off to two decimal places).

A general aviation airplane is initially in steady and level flight. The stability coefficient $ \frac{\partial C_m}{\partial q} $ (where $ C_m $ is the airplane pitching moment coefficient and $ q $ is the pitch rate) is negative. The airplane is perturbed with a small nose-up constant pitch rate. Assume that the horizontal tail does not stall during the perturbation, and unsteady effects are neglected. When compared to steady and level flight conditions, which of the following statements is/are true during the perturbed motion?

A general aviation airplane is flying at an altitude of 5000 m. The indicated airspeed is 250 km/h. Assume that there are no instrument errors and position errors. Neglecting compressibility effects, which one of the following options is FALSE?

To achieve longitudinal static stability of a general aviation airplane, which one of the following conditions should be satisfied?

For a general aviation airplane, which one of the following has a destabilizing effect on its static roll stability?

A jet-powered airplane is steadily climbing at a rate of 10 m/s. The air density is 0.8 kg/m³, and the thrust force is aligned with the flight path. Using the information provided in the table below, the airplane’s thrust to weight ratio is \_\_\_\_\_\_ (rounded off to one decimal place).
\includegraphics[width=0.5\linewidth]{52.png}

While taking off, the net external force acting on an airplane during the ground roll segment can be assumed to be constant. The airplane starts from rest. $ S_{LO} $ and $ V_{LO} $ are the ground roll distance and the lift-off speed, respectively. $ \alpha V_{LO} $ ($ \alpha>0 $) denotes the airplane speed at 0.5 $ S_{LO} $. Neglecting changes in the airplane mass during the ground roll segment, the value of $ \alpha $ is \_\_\_\_\_ (rounded off to two decimal places).

A general aviation airplane is initially in steady and level flight. The stability coefficient $ \frac{\partial C_m}{\partial q} $ (where $ C_m $ is the airplane pitching moment coefficient and $ q $ is the pitch rate) is negative. The airplane is perturbed with a small nose-up constant pitch rate. Assume that the horizontal tail does not stall during the perturbation, and unsteady effects are neglected. When compared to steady and level flight conditions, which of the following statements is/are true during the perturbed motion?

To achieve longitudinal static stability of a general aviation airplane, which one of the following conditions should be satisfied?

For a general aviation airplane, which one of the following has a destabilizing effect on its static roll stability?

A general aviation airplane is flying at an altitude of 5000 m. The indicated airspeed is 250 km/h. Assume that there are no instrument errors and position errors. Neglecting compressibility effects, which one of the following options is FALSE?

A jet-powered airplane is steadily climbing at a rate of 10 m/s. The air density is 0.8 kg/m³, and the thrust force is aligned with the flight path. Using the information provided in the table below, the airplane’s thrust to weight ratio is \_\_\_\_\_\_ (rounded off to one decimal place).
\includegraphics[width=0.5\linewidth]{52.png}

While taking off, the net external force acting on an airplane during the ground roll segment can be assumed to be constant. The airplane starts from rest. $ S_{LO} $ and $ V_{LO} $ are the ground roll distance and the lift-off speed, respectively. $ \alpha V_{LO} $ ($ \alpha>0 $) denotes the airplane speed at 0.5 $ S_{LO} $. Neglecting changes in the airplane mass during the ground roll segment, the value of $ \alpha $ is \_\_\_\_\_ (rounded off to two decimal places).

A general aviation airplane is initially in steady and level flight. The stability coefficient $ \frac{\partial C_m}{\partial q} $ (where $ C_m $ is the airplane pitching moment coefficient and $ q $ is the pitch rate) is negative. The airplane is perturbed with a small nose-up constant pitch rate. Assume that the horizontal tail does not stall during the perturbation, and unsteady effects are neglected. When compared to steady and level flight conditions, which of the following statements is/are true during the perturbed motion?

For a general aviation airplane, which one of the following has a destabilizing effect on its static roll stability?

In a conventional configuration airplane, the rudder can be used:

Which of the following statements about a general aviation aircraft, while operating at point $Q$ in the $V$-$n$ diagram, is/are true?