This is the code i have so far, plotted Figure $3$ has a jump in the middle of the graph that shouldn't be there, plotted figure $1$ is missing the black outline that shows the shape of the airfoil. The last reply i got on chegg the code was not all there$/$ was cut short

clear

clc

$\%$

naca$0012=$ struct$(\text{'}$m$\text{'},0,\text{'}$p$\text{'},0,\text{'}$tt$\text{'},12,$ 'chord$\_$length', $3)$; $\%$ NACA $0012$

naca$2412=$ struct$(\text{'}$m$\text{'},2,\text{'}$p$\text{'},4,\text{'}$tt$\text{'},12,$ 'chord$\_$length', $1\mathrm{.}5)$; $\%$ NACA $2412$

naca$5615=$ struct$(\text{'}$m$\text{'},5,\text{'}$p$\text{'},6,\text{'}$tt$\text{'},15,$ 'chord$\_$length', $2\mathrm{.}5)$; $\%$ NACA $5615$

$\%$ Calculation

$[$xc$0012,$ yc$0012,$ xU$0012,$ yU$0012,$ xL$0012,$ yL$0012]=$ calculate$\_$airfoil$\_$coordinates$($naca$0012)$;

$[$xc$2412,$ yc$2412,$ xU$2412,$ yU$2412,$ xL$2412,$ yL$2412]=$ calculate$\_$airfoil$\_$coordinates$($naca$2412)$;

$[$xc$5615,$ yc$5615,$ xU$5615,$ yU$5615,$ xL$5615,$ yL$5615]=$ calculate$\_$airfoil$\_$coordinates$($naca$5615)$;

$\%$ Plot

plot$\_$airfoil$($xc$0012,$ yc$0012,$ xU$0012,$ yU$0012,$ xL$0012,$ yL$0012,$ 'NACA $0012\text{'})$;

plot$\_$airfoil$($xc$2412,$ yc$2412,$ xU$2412,$ yU$2412,$ xL$2412,$ yL$2412,$ 'NACA $2412\text{'})$;

plot$\_$airfoil$($xc$5615,$ yc$5615,$ xU$5615,$ yU$5615,$ xL$5615,$ yL$5615,$ 'NACA $5615\text{'})$;

$\%$ Function to calculate airfoil coordinates

function $[$xc$,$ yc$,$ xU$,$ yU$,$ xL$,$ yL$]=$ calculate$\_$airfoil$\_$coordinates$($naca$)$

$\%$ Extract parameters

m $=$ naca.m $/100$;

p $=$ naca.p $/10$;

tt $=$ naca.tt $/100$;

c $=$ naca.chord$\_$length;

$\%$ Calculate coordinates

x $=$ linspace$(0,$ c$,850)$;

yc $=$ zeros$($size$($x$))$;

yt $=5*$ tt $*(0\mathrm{.}2969*$ sqrt$($x$/$c$)-0\mathrm{.}1260*($x$/$c$)-0\mathrm{.}3516*($x$/$c$).^2+0\mathrm{.}2843*($x$/$c$).^3-0\mathrm{.}1015*($x$/$c$).^4)$;

yt$($isnan$($yt$))=0$;

for i $=1$:length$($x$)$

if x$($i p$*$c

yc$($i$)=$ m $/$ p$^2*(2*$p$*$x$($i$)-$ x$($i$)^2)$;

dycdx $=2*$ m $/$ p$^2*($p $-$ x$($i$))$;

else

yc$($i$)=$ m $/(1-$ p$)^2*((1-2*$p$)+2*$p$*$x$($i$)-$ x$($i$)^2)$;

dycdx $=2*$ m $/(1-$ p$)^2*($p $-$ x$($i$))$;

end

theta $=$ atan$($dycdx$)$;

xc$($i$)=$ x$($i$)-$ yt$($i$)*$ sin$($theta$)$;

yc$($i$)=$ yc$($i$)+$ yt$($i$)*$ cos$($theta$)$;

end

xU $=$ xc $-$ yt $.*$ sin$($atan$((2*$m$*($x$/$p$).*(1-$x$/$c$)+$ dycdx$.*($c $-2*$x$/$c$))./(1+($dycdx$.*($x$/$c$)).^2)).\text{'})$;

yU $=$ yc $+$ yt $.*$ cos$($atan$((2*$m$*($x$/$p$).*(1-$x$/$c$)+$ dycdx$.*($c $-2*$x$/$c$))./(1+($dycdx$.*($x$/$c$)).^2)).\text{'})$;

xL $=$ xc $+$ yt $.*$ sin$($atan$((2*$m$*($x$/$p$).*(1-$x$/$c$)+$ dycdx$.*($c $-2*$x$/$c$))./(1+($dycdx$.*($x$/$c$)).^2)).\text{'})$;

yL $=$ yc $-$ yt $.*$ cos$($atan$((2*$m$*($x$/$p$).*(1-$x$/$c$)+$ dycdx$.*($c $-2*$x$/$c$))./(1+($dycdx$.*($x$/$c$)).^2)).\text{'})$;

end

$\%$ Function to plot airfoil

function plot$\_$airfoil$($xc$,$ yc$,$ xU$,$ yU$,$ xL$,$ yL$,$ label$)$

figure;

plot$($xU$,$ yU$,\text{'}$k$\text{'},$ 'LineWidth', $1\mathrm{.}5)$; hold on;

plot$($xL$,$ yL$,\text{'}$k$\text{'},$ 'LineWidth', $1\mathrm{.}5)$;

plot$($xc$,$ yc$,\text{'}$r$--\text{'},$ 'LineWidth', $1\mathrm{.}5)$;

plot$([$xc$(1),$ xU$(1)],[$yc$(1),$ yU$(1)],\text{'}$bo$\text{'},$ 'MarkerFaceColor', $\text{'}$b$\text{'},$ 'MarkerSize', $8)$;

plot$([$xc$($end$),$ xU$($end$)],[$yc$($end$),$ yU$($end$)],\text{'}$bo$\text{'},$ 'MarkerFaceColor', $\text{'}$b$\text{'},$ 'MarkerSize', $8)$;

grid on;

axis equal;

xlabel$(\text{'}$Chord Length'$)$;

ylabel$(\text{'}$Thickness$/$Camber$\text{'})$;

title$($label$)$;

legend$(\text{'}$Upper Surface', 'Lower Surface', 'Mean Camber Line', 'Location', 'Best'$)$;

end