If an airplane weighs 2,300 lbs, what approximate weight must it support during a 60-degree turn while maintaining altitude?

During a 60-degree turn, an airplane experiences increased load factor due to the centrifugal force acting on it. The load factor is defined as the ratio of the lift produced by the wings to the weight of the aircraft. When performing a turn, the required lift must not only counteract the airplane's weight but also provide the force necessary to maintain the turn.

At a 60-degree bank angle, the load factor increases significantly. Specifically, the load factor can be calculated using the formula:

Load Factor = 1 / cos(θ)

In this case, for a bank angle of 60 degrees, the cosine of 60 degrees is 0.5. Therefore, the load factor would be:

Load Factor = 1 / 0.5 = 2

This means that during a 60-degree turn, the airplane must produce twice its weight in lift to maintain altitude. Since the weight of the airplane is 2,300 lbs, the lift required during the turn will be:

Lift = Weight × Load Factor

Lift = 2,300 lbs × 2 = 4,600 lbs

Thus, the airplane must support approximately 4,600 lbs of lift during the turn while maintaining altitude, which corresponds to the choice