To understand why an airplane's center of gravity (CG) must be positioned in a specific location to maintain static stability, we must first comprehend the concepts of aerodynamic center and neutral point.
The aerodynamic center is the point on the wing or airfoil where the pitching moment coefficient remains constant regardless of the angle of attack. It is typically located near the quarter-chord point of the wing.
The neutral point is the aftmost CG location where the airplane remains statically stable. If the CG were at the neutral point, any shift aft would make the airplane neutrally stable—or even potentially unstable.
For an airplane to be statically stable, its center of gravity must be positioned such that an increase in angle of attack results in a restoring moment. This means the CG should be ahead of the neutral point.
Therefore, the correct statement is that for static stability, an airplane's center of gravity must always be ahead of the neutral point.
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).