An aircraft with wing loading $W/S = 2000\text{ N/m}^2$ executes a pull-up maneuver at a flight speed $V = 100\text{ m/s}$ in air of density $\rho = 1.0\text{ kg/m}^3$. If the maximum lift coefficient during the maneuver is $C_{L,\max} = 1.6$, what is the maximum available load factor $n_{\max}$?

Answer Key:

4.0

### Solution: Dynamic pressure $q = \frac{1}{2}\rho V^2 = \frac{1}{2}(1.0)(100^2) = 5000\text{ Pa}$. Maximum lift per unit area $L_{\max}/S = q C_{L,\max} = 5000 \times 1.6 = 8000\text{ N/m}^2$. Maximum load factor $n_{\max} = \frac{L_{\max}/S}{W/S} = \frac{8000}{2000} = 4.0$. Correct: 4.0.

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