Part $($b$)$

Some aeronautical engineers are designing an aircraft and wish to calculate the lift produced by their new wing design, Fig $3-$b$.$ The chord length $L_c$ of the wing is $1\mathrm{.}0$ m and its planform area A $($area viewed from the top when the wing is at zero angle of attack$)$ is $10m^2.$ The prototype is to fly at $V=50\frac{m}{s}$ close to the ground where $T=20C.$ They build a one tenth scale model of the wing to test in a pressurised wind tunnel. The wind tunnel can be pressurised to a maximum of $6$ atm $.$ At what speed and pressure should they run the wind tunnel in order to achieve dynamic similarity.