In this report, we propose a technique to adapt the shape parameterisation of an aircraft wing in the course of an optimisation of aerodynamic performanc- e. The M6 Onera transonic wing was chosen as a test case, in particular the objective of the optimisation was the minimisation of drag, keeping constant the lift and the total volume of the wing. In a first step, the parameterisation of the cross sections by Bézier curves consisted on keeping constant the control points abscissa distribution and changing the ordinates, while, in further steps, the constant abscissa distribution was modified, in order to regularise progressively the Bézier control polygon. Our numerical experiments have demonstrated that a self-adaptive parameterisation (i) permits to account for a larger set of feasible solutions, (ii) results in a quantitatively notably improved optimisation performance, and (iii) converges towards a non-intuitive distribution of control points, revealing the necessity and usefulness of self-adaptive algorithms.