This article investigates the aerodynamic performance increase of an Airbus A320 morphing aerofoil, having a chord of 70cm at Mach number 0.78 corresponding to cruise conditions and Reynolds number of 4.5 × 106. The morphing concepts involved vibration and slight deformation of the trailing edge region as well as actuation through travelling waves (TW) along a specific area of the suction side. These morphing concepts are integrated on the wing prototypes studied under the French “Agence Nationale de Recherche”-ANR project EMBIA - “Electrical Multiscale Bioinspired Interfaces in Aeronautics”, https://anr.fr/Project-ANR-21-CE05-0006 and in the context of the H2020 European project TEAMAERO, (“Towards Effective Flow Control and Mitigation of Shock Effects in Aeronautical Applications”) (https://cordis.europa.eu/project/id/860909/fr). The present paper analyses by means of numerical simulation the physical mechanisms leading to the increase of the lift-to-drag ratio as well as the drag and noise sources reduction. Frequency vibrations ranging from 250 Hz to 750 Hz and amplitudes in the order of 1 mm have been examined. Three angles of attack have been considered regarding the Trailing Edge (TE) actuation: 0°, 1.8°, and 2.4°, as well as the angle of 1.8° for the Travelling Wave (TW) actuation. This study analysed how these morphing concepts take advantage of feedback effects stemming from the near wake unsteadiness towards the Shock Boundary Layer Interaction (SBLI) region and even upstream of it and the reasons for obtaining a considerable aerodynamic performance increase. Among them, a lock-in mechanism of the transonic buffet oscillations on the vibration frequency has been obtained leading to a considerable lift-to-drag ratio and mitigation of the transonic buffet instability. These facts led to a drag reduction of 14% and an increase in aerodynamic efficiency (lift-to-drag ratio) by approximately 12 %.