Computations of Flow Near the Nose of Wing-body Junction

The paper considers the simulation of a flow around the wing installed on a flat plate. The wing is formed by symmetrical thick airfoil at zero angle of attack. The flow is deep subsonic with chord based \(Re\approx 10^{6}\) . The mathematical model tends to replicate conditions of the experimental setup. RANS approach and its eddy resolving counterpart, IDDES, show different simulation outcome. While SST RANS gives a steady state flow picture with a horse-shoe vortex and multiple secondary vortices, the SST IDDES approach reveals the unsteady bimodal nature if this system.