The center of gravity is located at xcg/ lref = 0.21.
Find the static margin in % of lref.
Derive the formula for the equilibrium incidence a(tt). Check your result carefully as other results depend upon it.
18.104.22.168 Take-Off Conditions
The take-off lift coefficient for the complete configuration is CL, to = 2.0. Find the tail setting angle and the incidence at take-off.
The tail lift curve is given by
CLt = 2.49a + 2.61tt – 0.36
Find the tail lift coefficient at take-off.
Find the lift force (in N) on the tail at take-off. Take p = 1.225 kg/m3. Is it up or down?
22.214.171.124 Extra Credit
Sketch qualitatively the forces (main wing and tail lifts, weight) and forces locations at take-off with respect to the aerodynamic centers of the main wing (xacm/ lref = 0.21), of the tail (xact /lref = 0.85), of the complete configuration (xac/lref) and with respect to the center of gravity.
14.5 Problem 6