$2\mathrm{.}3.$ Analyze the canard$-$wing combination shown in Figure $P2\mathrm{.}3.$ The canard and wing are geometrically similar and are made from the same airfoil section.

$A{R}_c=A{R}_w,S_e=0\mathrm{.}2S_w\frac{,}{b}ar(c{)}_c=\frac{0\mathrm{.}45}{b}ar(c{)}_w$

$($a$)$ Develop an expression for the moment coefficient about the center of gravity. You may simplify the problem by neglecting the upwash $($downwash$)$ effects between

$86$ CHAPTER $2$: Static Stability and Control

the lifting surfaces and the drag contribution to the moment. Also assume small angle approximations.

$($b$)$ Find the neutral point for this airplane.

rIGUKE TL$.$S