Large-eddy simulations were carried out to describe the subsonic flow over a wing section, using unsteady Coanda-jet circulation control to augment lift. The section geometry consists of a modified supercritical airfoil with a quarter-circular trailing-edge Coanda surface. Because the configuration does not include a slotted trailing-edge flap, the mechanical complexity and weight may be reduced. The computations correspond to an experimental investigation that collected only force measurements. High-fidelity solutions were obtained to the unsteady three-dimensional Navier–Stokes equations at a chord-based Reynolds of Formula: see text, a freestream Mach number of 0.1, and an angle of attack of 5.0 deg. As a means of decreasing jet mass-flow requirements, a discrete segmented jet arrangement is considered, and unsteady control is applied. Parametric studies are performed for the jet oscillation frequency and sweeping angle. Unsteady controlled results are compared to each other and with previously obtained steady blowing simulations for nonsegmented jets. Details of the simulations are described, and features of unsteady flowfields are characterized.
Rizzetta et al. (Sun,) studied this question.