Numerical Simulations of Low-Reynolds-Number Flow Past Finite Wings with Leading-Edge Protuberances

The use of various modeling approaches for the numerical simulation of low-Reynolds-number flow past wings of finite span with leading-edge protuberances is studied at pre- and poststall operating conditions. Variants of Reynolds-averaged Navier-Stokes simulations (including transitional modeling) and detached-eddy simulations (involving different options for shielding the boundary layer from the detached-eddy simulation limiter), as well as a low-Reynolds-number correction, are considered. An assessment of the capabilities exhibited by these modeling approaches is carried out, based on detailed comparisons against whole-flowfield and aerodynamic force measurements in a wind tunnel, at a Reynolds number of Re = 1.4 x 10(5) for wings with aspect ratios of 1 and 1.5. The results show that the use of detached-eddy simulation with an improved description of the boundary layer is required to reproduce the flow physics accurately at prestall conditions, where separation and subsequent reattachment are observed. At poststall regimes, massive flow separation occurs, and a choice of conservative shielding produces the best outcome with detached-eddy simulation. In addition, the present experimental dataset provides valuable information toward understanding the passive stall control mechanism generated by the use of leading-edge tubercles and its application to low-aspect-ratio wings.