Reduction of the specific consumption of aircraft would lead to substantial economic and environmental benefits. A promising technique consists in reducing skin friction drag by delaying the laminar-turbulent transition point as far aft as possible, particularly on the wings, in order to obtain lower friction coefficient in the presence of laminar flow. This can be achieved by Hybrid Laminar Flow Control (HLFC) technology. This paper presents the aerodynamic design of a largescale HLFC wing model for experiments that will be conducted in ONERA's S1MA wind-tunnel. The wing model is designed to investigate the major aerodynamic challenges that must be tackled to enable the development of HLFC airfoils: assessment in transonic flow conditions of the wing drag reduction due to HLFC suction, surface tolerance requirements on a HLFC wing and investigation of Attachment Line Contamination.