$($Show work and steps. Circle$/$box final answers$)$Problem $3$:

Given the following latera$($l$)/($d$)$irectional data for a jet aircraft:

C$\_($L$\_(0))=0,$C$\_($L$\_(\backslash$beta $))=-(0\mathrm{.}0732)/($r$)$ad$,$C$\_($L$\_(\backslash$delta a$))=(0\mathrm{.}0226)/($r$)$ad$,$C$\_($L$\_(\backslash$delta r$))=(0\mathrm{.}0029)/($r$)$ad

C$\_($N$\_(0))=0,$C$\_($N$\_(\backslash$beta $))=(0\mathrm{.}1638)/($r$)$ad$,$C$\_($N$\_(\backslash$delta a$))=(0\mathrm{.}0026)/($r$)$ad$,$C$\_($N$\_(\backslash$delta r$))=-(0\mathrm{.}0712)/($r$)$ad

where

Y : side$-$force

$\backslash$beta : side$-$slip angle

L: rolling moment

N : yawing moment

$\backslash$delta a : aileron deflection with

limits $-20\backslash$deg $,+20\backslash$deg

$\backslash$delta r : rudder deflection with

limits $-25\backslash$deg $,+25\backslash$deg

a