Abstract
Abstract This paper reviews important advances in understanding the different effects of supersonic combustion systems. The review mainly focuses on flame stabilization process. The first section describes the effect of equivalence ratio on dual mode ramjet to scramjet combustion system. The second sectiondiscusses theeffect of geometrical configuration of a supersonic combustor under various conditions of throttling mass flow rate. It is observed thathigher throttling mass flow could gave a better flame stability and ignition performance. The third section explains the influence of cavity configurations on supersonic combustor.It can be adjudged from the review that the larger cavity configurations could gave abetter ignition performance, air-fuel mixing enhancement and rich blow out limit (RBL).
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