Which angle of attack would likely result in the lowest drag for a specific aircraft configuration?

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The angle of attack (AoA) that results in the lowest drag for a specific aircraft configuration is typically found close to the point where the airflow remains smooth over the wings, allowing for efficient lift generation with minimal resistance.

At zero degrees of angle of attack, although the aircraft is in a horizontal flight position, it might not produce enough lift, causing the aircraft to stall or fall below the optimal performance zone. As the angle of attack increases from zero to around 2 degrees, lift starts to increase, and drag remains relatively low.

At 2 degrees, the airflow remains attached to the wing surface, allowing for efficient operation with a good lift-to-drag ratio. This is usually where the aircraft can achieve its best performance in terms of drag reduction while still generating adequate lift. The angle of attack beyond this point increases both lift and drag, and while some drag is still manageable, it tends to rise more significantly as the angle approaches higher values, such as 4 degrees or 10 degrees.

At 4 degrees and particularly at 10 degrees, the aircraft may start experiencing increased induced drag due to the higher lift required to maintain smooth airflow and prevent stalling. Therefore, 2 degrees is likely the angle at which the balance

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