The Piper Cherokee $($a light, single$-$engine general aviation aircraft$)$ has a wing area of $\backslash (170\backslash$mathrm$\{$ft$\}^\{2\}\backslash )$ and a wing span of $32$ ft $.$ Its maximum gross weight is $2450$ lb $.$ The airplane is cruising at $\backslash (117\mathrm{.}0\backslash$mathrm$\{$mi$\}/\backslash$mathrm$\{$h$\}\backslash )$ at standard sea level at its maximum gross weight and is in straight$-$andlevel flight. The span efficiency factor $\backslash ($ e $\backslash )$ for the complete airplane is generally much less than that for the finite wing alone. Assume $\backslash ($ e$=\backslash )0\mathrm{.}64.$ Calculate the induced drag for the airplane. $($Round the final answer to three decimal places.$)$

The induced drag for the airplane is

lb$.$