Aerodynamics: $3\mathrm{.}19$ A typical World War I biplane fighter $($such as the French SPAD shown in Figure $3\mathrm{.}50)$ has a number of vertical interwing struts and diagonal bracing wires. Assume for a given airplane that the total length for the vertical struts $($summed together$)$ is $25$ ft $,$ and that the struts are cylindrical with a diameter of $2$ in $.$ Assume also that the total length of the bracing wires is $80$ ft $,$ with a cylindrical diameter of $\frac{3}{32}in.$ Calculate the drag $($in pounds$)$ contributed by these struts and bracing wires when the airplane is flying at $120m\frac{i}{h}$ at standard sea level. Compare this component of drag with the total zero$-$lift drag for the airplane, for which the total wing area is $230f{t}^2$ and the zero$-$lift drag coefficient is $0\mathrm{.}036.$