A YF$-23$ with a double$-$wedge airfoil is cruising at $60,000$ ft at Mach $1\mathrm{.}58.$ That atmospheric conditions are that of a Standard Day at this altitude. The wave drag is $D_{\text{w}\text{a}\text{v}\text{e}}=7,700lbs.$ The wing area is $S=900$ sq$.$ ft $.$ Assume that this is the exposed wing area. At this speed, half of the $D_{\text{w}\text{a}\text{v}\text{e}}$ is due to thickness. From this value, please estimate the $\frac{t}{c}($thickness to chord ratio$)$ of the wing section.

Please remember to use the correct formulation for dynamic pressure as a function of Mach Number!