Consider an aircraft with a rectangular wing and a

rectangular horizontal stabilizer as shown in the

diagrams below. Three different horizontal

stabilizer locations are being considered: a low

tail, mid tail and high tail, labeled A$,$ B$,$ and C

respectively in the drawing. All of the stabilizers

have the same longitudinal location $($as shown in

the top view$),$ but have different vertical locations

relative to the wing zero lift line $($as shown in the

side view$).$

If the CG is located at $35\%$ chord, what is the

static margin for each case?

You can ignore the effects of the fuselage,

propulsion system, and vertical stabilizer. Include

the carry$-$through section of the wing in the wing

planform area.

Assume the airfoil lift slope is $6\mathrm{.}28ra{d}^{-1}$ and then

do a finite wing correction to find the lift slope of

both wing and stabilizer. Use efficiency factor $e=$

$0\mathrm{.}8$ in both cases.

$a=\frac{c_{l_{}}}{1+\frac{c_{l_{}}}{*AR*e}}$

Assume the aerodynamic centers of both the wing and the stabilizer are located at quarter chord.

Use appendix B$.5$ of Etkin and Reid to estimate the downwash parameter for each stabilizer

location. This will have an impact on the static margin values.