Consider the Supermarine Spitfire. Its maximum velocity is $\backslash (362\backslash$mathrm$\{$mi$\}/\backslash$mathrm$\{$h$\}\backslash )$ at an altitude of $19,000$ ft $.$ Its weight is $5820$ lb $,$ wing area is $242\backslash (\backslash$mathrm$\{$ft$\}^\{2\}\backslash ),$ and wing span is $36\mathrm{.}1$ ft $.$ It is powered by a supercharged Merlin engine, which produced $1050$ horsepower at $19,000$ ft $.$ The induced drag coefficient of the Spitfire is $0\mathrm{.}001.$ If the elliptical wing of the Spitfire were replaced by a tapered wing with a taper ratio of $0\mathrm{.}4,$ calculate the induced drag coefficient and the percentage increase with the given value.

The following graph is a plot of induced drag factor $\backslash (\backslash$delta $\backslash )$ as a function of taper ratio.

The induced drag coefficient is

$.($Round the final answer to three decimal places.$)$

The percentage increase is

$\backslash \%.$