(Solved): Example 2-4 Lift on a Wing: Fig. 2-16 Lift FL on a wing of chord length Lc free-stream speed ...

Example 2-4 Lift on a Wing: Fig. 2-16 Lift $F_L$ on a wing of chord length $L_c$ free-stream speed $\mathrm{V}$ with density $?$, viscosity $?$, and speed of sound c. The angle of attack $?$ is measured relative to the free-stream flow direction. Some aeronautical engineers are designing an airplane and wish to predict the lift produced by their new wing design (Fig. 2-16). The chord length $L_c$ of the wing is $1.12\mathrm{m}$, and its planform $\mathrm{area}A$ (area viewed from the top when the wing is at zero angle of attack) is $10.7{\mathrm{m}}^2$. The prototype is to fly at $V=52.0\mathrm{m}/\mathrm{s}$ close to the ground where $T$ $=25^{?}\mathrm{C}$. They build a one-tenth scaled model of the wing to test in a pressurized wind tunnel. The wind tunnel can be pressurized to a maximum of $5\mathrm{atm}$. At what speed and pressure should they run the wind tunnel in order to achieve dynamic similarity?