Rectangular wing with $5$ ft span and $1\mathrm{.}2$ ft chord utilizes NACA $63-210$ airfoil uniformly along the span.

$1.$ Find alpha and D if the lift is $10$ lbf for a speed of $35$ mph$.$ Assume lift is uniformly distributed along span and neglect induced drag.

$2.$ Calculate induced drag based on the same conditions.

$3.$ Calculate the lift$/$total drag ratio.

Include formula, substitution, and solution for each equation. Use charts as needed, indicate when chart was used.