Leading edge systems of long–haul aircraft wings extend the operational envelope in terms of flight speed, range, and fuel efficiency, while also enhancing flight safety by providing protection against external loads and harsh environmental conditions. Accordingly, leading edge concepts combining the functions of high lift, gust and manoeuvre load alleviation (GLA and MLA) and active drag reduction based on hybrid laminar flow control (HLFC) are being investigated, along with secondary functions such as protection against icing, bird strikes, insect contamination and lightning strikes. In previous research, at least partial combinations of these different leading edge functions have already been demonstrated [1, 2, 3, 4, 5, 6], but a fully integrated multifunctional solution has not yet been realised. The present work addresses the computational, aerostructural design and optimisation of a multifunctional leading edge system (MFLES). Based on general system requirements, three distinct concepts are derived: a fully morphing droop nose, as well as inward and outward semi-morphing droop noses. A multidisciplinary optimisation framework is applied to achieve optimal shape adaptation of a laminar transonic airfoil (2D). Airfoil geometry parameters and MFLES deflection angles for take-off conditions are optimised using a low-fidelity aerodynamics tool, targeting enhanced lift characteristics, improved low-speed aerodynamic efficiency, and delayed flow separation. Structural characteristics are evaluated using the Chained Beam Constraint Model [7] and Finite Element Analysis, aiming to minimise deformation power consumption (for both high lift and GLA/MLA) and structural mass, while identifying favourable kinematic actuation point locations. The sensitivity of the results to key design parameters is analysed, including implications for kinematics, actuation and HLFC system layout. On this basis, the most suitable droop nose concept among the three is selected.