$9\mathrm{.}43$ Plot the ight envelope $($combined V$-$n diagram$)$ for the following GA normal aircraft. Then, determine the

maximum load factor. Assume the maximum positive and negative limit maneuvering load factors to be $+3\mathrm{.}5$

and $1\mathrm{.}5,$ respectively.

m $=1800$ kg$,$ S $=14$ m$2,$ CLmax $=1\mathrm{.}8,$CLmax $=0\mathrm{.}9,$ AR $=6,$ CL$\backslash$alpha $=$ a $=41/$rad$,$

Vc $=280$ KEAS $($at $20,000$ ft$)$