The load factor during a constant altitude turn is primarily determined by:

The load factor during a constant altitude turn is primarily determined by the bank angle alone. This is because when an aircraft turns while maintaining altitude, the required lift must increase to counteract the horizontal component of lift that is necessary to execute the turn. The relationship between bank angle and load factor is a fundamental principle in aerodynamics.

As the bank angle increases, the load factor also increases. This happens because, in a turn, gravity acts downward while the lift vector tilts towards the inside of the turn, creating a need for greater lift to maintain altitude against the pull of gravity. Specifically, the load factor can be calculated using the formula: Load Factor (n) = 1 / cos(θ), where θ is the bank angle. Thus, a steeper bank requires a greater lift to maintain altitude, which translates to a higher load factor.

While other factors such as aircraft weight, speed, and altitude influence overall flight performance, they do not directly determine the load factor in a turn as significantly as the bank angle does. Therefore, understanding the importance of bank angle is critical for pilots to manage their aircraft during maneuvers and to avoid exceeding the aircraft’s structural limits.