$2\mathrm{.}8.$ Estimate the fuselage and engine nacelle contribution to $C_{m_0}$ using the method discussed in section $2\mathrm{.}3$ for the STOL transport shown in Figure P$2\mathrm{.}8.$ The airplane has

Problems

$89$

been divided into $12$ sections as indicated in Figure P$2\mathrm{.}8.$ The section length, width, and distance from the wing leading or trailing edge to the midpoint of each section is given in the table below. The engine nacelles have been approximated by one section as indicated on the figure.

$\backslash$table$[[,$Fuselage$],[$Station$,xft,w_{f}ft,x_{i}ft$