TY - JFULL AU - Rakesh Arasu and Sasitharan Ambicapathy and Sivaraj Ponnusamy and Mohanraj Murugesan and V. R. Sanal Kumar PY - 2013/9/ TI - Numerical Studies on Flow Field Characteristics of Cavity Based Scramjet Combustors T2 - International Journal of Aerospace and Mechanical Engineering SP - 1720 EP - 1727 VL - 7 SN - 1307-6892 UR - https://publications.waset.org/pdf/16233 PU - World Academy of Science, Engineering and Technology NX - Open Science Index 80, 2013 N2 - The flow field within the combustor of scramjet engine is very complex and poses a considerable challenge in the design and development of a supersonic combustor with an optimized geometry. In this paper comprehensive numerical studies on flow field characteristics of different cavity based scramjet combustors with transverse injection of hydrogen have been carried out for both non-reacting and reacting flows. The numerical studies have been carried out using a validated 2D unsteady, density based 1st-order implicit k-omega turbulence model with multi-component finite rate reacting species. The results show a wide variety of flow features resulting from the interactions between the injector flows, shock waves, boundary layers, and cavity flows. We conjectured that an optimized cavity is a good choice to stabilize the flame in the hypersonic flow, and it generates a recirculation zone in the scramjet combustor. We comprehended that the cavity based scramjet combustors having a bearing on the source of disturbance for the transverse jet oscillation, fuel/air mixing enhancement, and flameholding improvement. We concluded that cavity shape with backward facing step and 45o forward ramp is a good choice to get higher temperatures at the exit compared to other four models of scramjet combustors considered in this study. ER -