If an accelerated stall occurs in a steep turn, how will the aircraft respond?

When discussing the dynamics of an accelerated stall occurring during a steep turn, it is crucial to understand the relationship between the aircraft's angle of attack, load factor, and how these factors affect the airflow over the wings. In a steep turn, the aircraft experiences increased load factor, meaning that both wings must generate more lift to maintain the turn. This increase in load factor results in higher angles of attack.

In a coordinated turn, both wings are generally at similar angles of attack. However, if the aircraft enters a slip – where the aircraft is intentionally uncoordinated and has a horizontal component of lift that is not aligned with the turn – the physics change. In this situation, the high wing (the wing farthest from the center of the turn) actually experiences a greater angle of attack compared to the low wing, which can lead to the high wing stalling first.

Conversely, during a skid – where the aircraft is also uncoordinated, but the yawing motion is opposite to the turn – the low wing typically encounters a higher angle of attack. Hence, it would stall first.

In coordinated flight, both wings are maintained at similar angles of attack, and they stall almost simultaneously because they are experiencing the same aerodynamic conditions.

This