Airfoils are the most important elements of an aircraft wing, having a chord length a camber and a thickness distribution. Traditionally, airfoils were being developed by empirical methods taking considerable support from wind tunnel testing. The ratio of lift to drag indicates the efficiency of an aerofoil. The purpose of this study is to adequately acquaint, as a first step, with a validated vertex lattice method code, the X-foil for computation of viscous flow over three aerofoils at different Reynolds numbers viz. 2.0×106, 3×106 and 6×106 Re respectively. In the second step, we consider in detail the impact of thickness-to chord ratio on the airfoil characteristics, choosing the NACA (National Advisory Committee for Aeronautics) five digit aerofoils, namely, 23012, 23015, 23021 as an applicant's approval of the commercial software to be utilized, is a vital stride to this review. Here we used the commercial software tool, the ANSYS FLUENT for the two-dimensional viscous flow, along with ICEM CFD for generation of suitable structured grids. NACA 23012 airfoil has been used in the validation of the software since extensive assemblage of writing exists for this traditional airfoil alongside solid wind test tunnel results at Reynolds number of 6 million [1]. Keywords: CFD, VLM, Re, Y+, lift, dragCite this Article Manjunath IB, Kulkarni Venkatesh M, Mallik Prasad NS et al. Studies on Thick Aerofoils at Subsonic Speeds for a Civil Transport Wing. Recent Trends in Fluid Mechanics. 2017; 4(1): 28–37p.
