Equilibrium of the AMAT11
The AMAT11 has a rectangular main wing with span bm = 2.1m and constant chord cxm = 0.3 m. The tail is also rectangular with span bt = 1.0 m and chord cxt = 0.3 m. The equilibrium code provides the aircraft characteristics and a maximum take-off mass M = 19 kg. The reference area is Aref = Am + At.
220.127.116.11 Aspect Ratios of Lifting Elements—Global Lift Slope
The aspect ratio of the wing, ARm and of the tail, ARt are computed as
ARm = — = 7.0, ARt = — = 3.33
the global lift slope dCL/da for the wing+tail configuration will be
18.104.22.168 Airplane Center of Gravity
The aerodynamic center is located at xa. c./lref = 0.3.
The center of gravity xc. g./lref, given a 6% static margin (SM) will be such that
Xc^ = — – 0.06 = 0.24