Computational investigation into vortex breakdown over a pitching delta wing at supersonic speeds

Vortex breakdown in compressible ows over a 60-degree sweep delta wing with a sharp leading edge undergoing pitching oscillations is computationally studied. Emphasis in this study is on possible supersonic vortex breakdown for pitching motion of a delta wing, as well as behavior of the aerodynamic characteristics during a cycle. Unstructured grid, k ?? !SST turbulence model, and dual-time implicit time integration are used. Accurate simulations are performed for various Mach numbers and mean angles of attack to cover dierent ow structures and phenomena associated with them. Variations of ow structure around the wing and hysteresis loops associated with lift coecient and vortex breakdown location during a pitching cycle are investigated. The trends with Mach number, mean angle of attack, amplitude of pitching, and pitching frequency are illustrated.