What is the static pressure distribution about a positively cambered airfoil at zero angle of attack in level flight?

In the context of a positively cambered airfoil at zero angle of attack in level flight, the characteristics of the airflow around the airfoil dictate that the static pressure will vary across its surfaces. A positively cambered airfoil is designed so that its upper surface is curved more than its lower surface. This curvature causes the air traveling over the upper surface to speed up, due to the principle of continuity and Bernoulli's equation.

According to Bernoulli's principle, as the velocity of a fluid increases, its static pressure decreases. Therefore, when the airflow moves faster over the upper surface of the positively cambered airfoil, it creates a region of lower static pressure compared to the lower surface, where the airflow is slower. The reduction of static pressure on the upper surface relative to the lower surface generates lift, which is fundamental in sustaining the aircraft in flight.

Thus, the correct assertion is that the static pressure distribution is less over the upper surface of the airfoil, which aligns with the aerodynamic behavior expected in this scenario.