This is the code i have, and figure $1$ is missing the upper and lower profile, figure $3$ has a jump in the graph. Could you fix the issues with my code and give the full new code. my code is below,

nacas $=[$

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

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

struct$(\text{'}$m$\text{'},5,\text{'}$p$\text{'},6,\text{'}$tt$\text{'},15,$ 'chord$\_$length', $2\mathrm{.}5)$

$]$;

$\%$ Calculations and Plots

for i $=1$:numel$($nacas$)$

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

plot$\_$airfoil$($xc$,$ yc$,$ xU$,$ yU$,$ xL$,$ yL$,[\text{'}$NACA $\text{'}$ num$2$str$($nacas$($i$).$m$)$ num$2$str$($nacas$($i$).$p$)$ num$2$str$($nacas$($i$).$tt$)])$;

end

$\%$ Function

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

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

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

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

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

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

else

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

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

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

$\%$ Plot Function

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