$2\mathrm{.}20$ Estimate the roll moment coefficients induced by the wake of a Boeing $747$ on several smaller

aircraft listed below. Use the data at sea level in Appendix B$.$ Compare the induced roll moment

coefficients to the maximum roll moment coefficients that could be developed by full aileron

deflection. Assume the aileron maximum deflection is $+-25$ for each aircraft. Use the problem

statement $2\mathrm{.}19$ and the expression for roll moment coefficient due to wake vortices as shown below

$C_l=\frac{-C_{L_{}}{c}_r}{u_{0}Sb}[(-1)\frac{b}{4}+\frac{b}{2}]$

a$)$ Convair $880$: $c_r=33\mathrm{.}6ft,=0\mathrm{.}2$

b$)$ STOL transport: $c_r=22ft,=0\mathrm{.}45$

c$)$ Business jet: $c_r=15\mathrm{.}3ft,=0\mathrm{.}32$

d$)$ The NAVION: $c_r=7\mathrm{.}7ft,=0\mathrm{.}6$