Final answer:
Minimum fuel for a go-around depends on the aircraft's weight, wing area, and the climb attitude. The specific values for minimum fuel per wing and max climb attitude may vary between different aircraft models. To calculate the minimum fuel per wing, you generally use the lift coefficient (CL) and adjust for specific conditions such as air density, speed, and wing area.
Step-by-step explanation:
Minimum fuel for a go-around depends on the aircraft's weight, wing area, and the climb attitude. The specific values for minimum fuel per wing and maximum climb attitude may vary between different aircraft models. However, to calculate the minimum fuel per wing, you generally use the lift coefficient (CL) and adjust for specific conditions such as air density, speed, and wing area.
An example: Assume a wing area of 20 square meters. If the aircraft is designed to produce 1000 N of lift per square meter, the total lift produced by both wings would be 20 * 1000 N = 20,000 N. Keep in mind that this is a simplified example, and real-world calculations would consider additional factors.
Regarding the max climb attitude, it is the angle at which the aircraft climbs efficiently while maintaining an acceptable airspeed. This angle is generally determined by the aircraft's design and the engine's power-to-weight ratio. It ensures that the aircraft remains within the acceptable performance envelope while ascending.