Comparative Assessment of the Combustion Property of a Cavity-Based Scramjet Combustor with Strut and Wall Injection Technique

Abstract

AbstractIn addition to the impact of combustion in the scramjet combustion system, the strut and wall injection system also supports to resolve the problem of heat transfer. The current research analytically examines the effect of a scramjet combustor on cavity and wall injection system. Outflow situations are 610 kPa, 1320 K, and 2.5, individually for stagnant temperature, stagnating pressure, and Mach number. The shock wave formation mechanism is evaluated. In addition, comparative analysis is conducted with the strut and wall injection techniques of combustion characteristics. The results indicate that the combustion and mixing probabilities are improved by using the strut injection system in the combustion unit. This study covered the CFD analysis in SCRAMJET engine discourse (supersonic ramjet combustion). Inventive air expiratory engines as the SCRAMJET motor were designed based on the knowledge of supersonic combination, self-ignition, and fire. These aero-thermo-motor processes are particularly hard to incorporate in a scramjet engine. Tribal grid converter, 3D Euler, and Navier-Stoke algorithm technologies were presented using complex analytical and mechanical models. A series of Mach estimates, the angle of attacks, was applied to various complicated aerodynamic flows for this indigenous programmed. CFD approaches are being developed as an effective method for manufacturing aerospace vehicles. Important science and computer studies also concentrate on injector analysis, which can contribute to rapid air and fuel blending and ignition.KeywordsSCRAMJET engineAerospace vehiclesComputational fluid dynamicsCombustorMach number