A wing section has the characteristics

shown in Fig. $11\mathrm{.}11$ and is intended to be used

as an airplane wing; it has a chord

of $244$ m and $14\mathrm{.}65$ m in length on each wing. The wings will have to support an airplane weighing $6500$ kg$.$ a$)$ Determine

the angle of attack necessary to fly

at $112$ km$/$h in standard atmosphere. b$)$ Determine the power necessary to overcome

the drag of the wings under these conditions.

Figura $11\mathrm{.}11.$ Coeficientes t$$picos de sustentaci$$n y arrastre, para un perfil de ala, para $Re=3{10}^6.$