Instructions: These problems are based on the static longitudinal stability of wing, tail with elevator deflection

$1.$ Consider the general aviation aircraft Cessna $172.$ Please use ChatGPT to obtain key geometrical and aerodynamic parameters of the aircraft. For example, you can ask questions such as What is the wingspane of the Cessna $172?,$ What is the ratio of tail to wing dynamic pressure of the Cessna $172?,$ What is the lift$-$curve slope of the Cessna $172?.$ In many cases, ChatGPT will give you the precise value. In some cases, it will give a range. If a range is provided, use a value of your choice in the given range.

$($a$)$ Tabulate all the relevant parameters you need for the stability analysis. You may add on to this list as you work out each of the following parts.

$($b$)$ Without a tail, does the Cessna $172$ possess longitudinal stability?

$($c$)$ If the location of the center of gravity is $2$ ft ahead of the leading edge of the wing, determine the $\backslash ($ C$\_\{$m$\_\{\backslash$alpha$\}\}\backslash )$ at these conditions.

$($d$)$ Does the value you get agree with what ChatGPT tells? You can ask the question What is the slope of moment coefficient versus angle of altack for Cessna $172?$

$($e$)$ Determine the neutral point of the Cessna $172.$

$($f$)$ Is your answer for the neutral point consistent with what ChatGPT tells? You can ask the question Where is the neutral point for the Cessna $172?$

$($g$)$ Compute the trim angle of attack and elevator deflection for the Cessna $172.$ You can utilize the trim $\backslash ($ C$\_\{$L$\}\backslash )$ at cruise provided by ChatGPT.

$($h$)$ Compare the results obtained for trim angle of attack and elevator deflection with those provided by ChatGPT.