Computational Study of Oblique Shock Induced Detonation Wave Stabilization by Deflection of Wedge Surface

The Development of supersonic combustor for hypersonic air breathing propulsion devices involves the study of shock-induced combustion. The mechanism intends to minimize the combustor length. The mechanism involves sufficient entropy generated behind Oblique Shock Wave (OSW) and this will ignite the premixed flow of fuel and air just beneath the OSW. Thus an Oblique Detonation Wave (ODW) formed. The formation and stabilization of ODW depend on free stream flow conditions and wedge angle. Free stream mixed flow should provide minimum entropy generation required for the combustion process and wedge angle, normal Mach number one. This condition is called as Chapman–Jouguet (C-J). One of the methods to stabilize the ODW is deflecting the wedge surface to make it parallel to free stream flow conditions. This leads to the interference of ODW with expansion fan and results in stabilization. The present research paper's objective is to simulate the proof of concept related to stabilization over finite length wedge. Free stream flow consists of stoichiometric mixture of hydrogen (fuel) and air. A near C-J condition free flow considered from literature. Two-dimensional CFD simulations carried using ANSYS CFX, CFD software based on Finite Volume Method. Hexagonal mesh adopted to capture the flow conditions and generated by ICEM CFD, an advanced meshing software. The chemical reactions modeling is based on multi step Jachimowski's finite rate chemistry models.