What is the maximum load factor typically used in aircraft design calculations?

In aircraft design calculations, a load factor of 3.8 is typically used to account for the extreme maneuvers that an aircraft may experience. This value represents the maximum load factor that the aircraft is designed to withstand in conditions where high g-forces are present, such as during sharp turns, sudden climbs, or descents.

Using a load factor of 3.8 helps ensure that the structural components of the aircraft can endure these stresses without failure. This ensures both safety and performance, allowing the aircraft to react resiliently under the dynamic loads encountered during various phases of flight.

In contrast, while a load factor of 1.5 for normal operations may apply to routine flying, it does not encompass the peak stress conditions. Similarly, a load factor of 5.0 would imply a higher design capability that is typically not required or feasible for standard aircraft operations, and a load factor of 2.0 for moderate turbulence would be insufficient to account for the stresses experienced during extreme maneuvers. Hence, 3.8 is the appropriate load factor used in design to ensure structural integrity and safety in challenging flight situations.