Consider a finite wing, which uses a NACA0012 airfoil cross-section, with an aspect ratio of 7, a taper ratio of 0.5 and
Posted: Mon May 02, 2022 3:09 pm
Consider a finite wing, which uses a NACA0012 airfoil
cross-section, with an aspect ratio of 7, a taper ratio of 0.5 and
a wing surface area of 2.625 m2. Using a 3-term
series to represent the load distribution, find the lift
coefficient and induced drag coefficient, for an angle of attack a
= 3ยบ. Sketch the wing.
cross-section, with an aspect ratio of 7, a taper ratio of 0.5 and
a wing surface area of 2.625 m2. Using a 3-term
series to represent the load distribution, find the lift
coefficient and induced drag coefficient, for an angle of attack a
= 3ยบ. Sketch the wing.