Case Study Part $4$a

This is a continuation of Part $4-$ you will need that tutorial set. The data is as given previously, except where stated below.

The objective here is to investigate further features associated with longitudinal static stability. Some questions refer to an unstable aircraft.

$1$ For question $3$ of Tutorial Set $7$ calculate $C_{LW}$ and $C_{LT}.$

$0\mathrm{.}89,0\mathrm{.}301$

$2$ For question $3$ of Tutorial Set $7$ calculate the aircraft trim angle of incidence ${}_a,$ and lift coefficients $C_{LW}$ and $C_{LT},$ but for $i_T=3.$

$-1\mathrm{.}5,0\mathrm{.}28,0\mathrm{.}034$

$3$ For the case of question $2$ above calculate the speed $V($EAS$).$

$131\mathrm{.}8\frac{m}{s}$

$4$ For question $3$ of Tutorial Set $7$ calculate $d\frac{C_M}{d_a}$ for a reduced tail plane surface area of i$)2m^2,$ii$)1m^2$

$-0\mathrm{.}00072,+0\mathrm{.}0056$

$5$ For the aircraft of Part $4($Tutorial Set $7)$ calculate the neutral point. Calculate $d\frac{C_M}{d_a}$ when $h=0\mathrm{.}3.$ If $i_T=5,$ calculate the aircraft trim angle of incidence ${}_a$ and the trim speed $($EAS$).$

$0\mathrm{.}233,+0\mathrm{.}00578,0\mathrm{.}2,104\mathrm{.}6\frac{m}{s}$

$6$ For the aircraft of Part $4($Tutorial Set $7),$ but with $h=-0\mathrm{.}1,$

i$)$ calculate ${}_a$ at trim and $C_{LT}$ for an $i_T$ of $1.$

ii$)$ calculate $i_T$ for an aircraft speed of $200\frac{m}{s}$ EAS.

$-1\mathrm{.}9,-0\mathrm{.}15,2\mathrm{.}35$