Laminar flow is a potential way of minimizing drag and reducing aircraft emissions. However, the interaction of laminar boundary layers with shock waves at transonic speeds can cause severe detrimental aerodynamic effects and remains an opened question. In this way, in the framework of the TFAST European project, a laminar transonic airfoil has been developed for both numerical and experimental studies on such laminar interactions. The so-called V2C profile has been studied to provide natural laminar flow from the leading edge to the shock wave for a wide range of freestream Mach numbers and angles of attack. In the present paper, a numerical investigation of the transonic flow around the V2C airfoil is conducted by means of URANS and hybrid RANS-LES computations. At sufficiently-high angles of attack and moderate freestream Mach number (0.70), the transonic interaction develops buffet. In the paper, special attention is paid to the differences between the URANS and hybrid RANS-LES predictions of the shock-induced separation.