Computational investigation of the flow structure over a pitching delta wing at supersonic speeds

Abstract

Compressible flows over a 60° sweep delta wing with a sharp leading edge undergoing pitching oscillations are computationally studied. Emphasis in this study is on possible supersonic flow structures and their variations during the pitching motion of a delta wing. Unstructured grid, [Formula: see text] turbulence model and a dual-time implicit time integration are used. Accurate simulations are performed for various Mach number and angles of attack to cover different flow structures and phenomena associated with them. Variations of flow patterns in a crossflow plane, pressure coefficient on the wing surface, and hysteresis loops associated with vortex core location during a pitching cycle are investigated. The trends with Mach number, mean angle of attack, amplitude of pitching and pitching frequency are illustrated.