This paper investigates a novel method of control for ‘morphing ’ aircraft. The concept consists of a pair of winglets with adaptive cant angle, independently actuated, mounted at the tips of a flying wing. Computations with a vortex lattice model and wind tunnel tests demonstrate the validity of the concept. The variable cant angle winglet appears to be a multi-axis effector with a favorable coupling in pitch and roll with regard to turning manoeuvres. Nomenclature α angle of attack δe elevator deflection angle η reduced spanwise coordinate Γ vortex strength γl, γr left and right winglet cant angles Γx vortex strength sensitivity w.r.t. variable x Ω turn rate φ bank angle ρ air density b wing span CD, CY, CL drag, side-force and lift coefficients Cl, Cm, Cn rolling, pitching and yawing moment coefficients CDx, CYx, CLx drag, side-force and lift coefficient derivatives w.r.t. parameter x Clx, Cmx, Cnx rolling, pitching and yawing moment coefficient derivatives w.r.t. parameter x croot root chord g gravitational acceleration p, q, r aircraft rotation rates in body or stability axes R turn radius u, v, w aircraft velocity components in body or stabilty axes Vcg flight speed W aircraft weight CG center of gravity LE leading edge TE trailing edge I
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