Final answer:
The aerodynamic principles relevant to an airfoil's performance are Bernoulli's principle and lift. The air moving over the upper surface of the airfoil must have lower pressure compared to the air moving under the lower surface, creating lift. The airspeed required to generate the ideal lift can be calculated using the lift equation.
Step-by-step explanation:
The aerodynamic principles relevant to an airfoil's performance include Bernoulli's principle and the concept of lift. According to Bernoulli's principle, as the airfoil moves through the air, the air moving over the upper surface must have a lower pressure compared to the air moving under the lower surface. This pressure difference generates lift, which allows the airfoil to stay aloft.
The speed at which air must move over the upper surface of the airfoil to create the ideal lift can be determined using the equation:
Lift = (1/2) x ρ x V² x A x CL
Where ρ is the air density, V is the airspeed relative to the airfoil, A is the wing area, and CL is the lift coefficient.
Therefore, by rearranging the equation to solve for V, the airspeed required can be calculated.