The rolling moment due to side slip is called
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- dihedral effect
- anhedral effect
- adverse yaw
- dutch roll
The Correct Option is A
Solution and Explanation
Top Questions on Aircraft 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).
- GATE AE - 2025
- Flight Mechanics
- Aircraft Stability
- 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).
- GATE AE - 2025
- Flight Mechanics
- Aircraft Stability
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).
- GATE AE - 2025
- Flight Mechanics
- Aircraft 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).
- GATE AE - 2025
- Flight Mechanics
- Aircraft Stability
- 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?
- GATE AE - 2025
- Flight Mechanics
- Aircraft Stability
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