Problem $1$

The NACA $63-210$ airfoil had good lift and stall characteristics as well as superior low$-$drag characteristics over a limited range of attack angles.

A rectangular wing having a $5\mathrm{.}0$ ft span and a $1\mathrm{.}2$ ft chord utilizes this airfoil uniformly along the span.

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

$2.$ For the same conditions calculate the induced drag.

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