<p>A numerical investigation is conducted to analyze the impact of increasing inflow air total temperatures on a scramjet combustor featuring a strut injector and cavity integration. The AnsysFluent tool is used for the computational analysis, employing RANS equations and an SST k-ω turbulence model. The cavities, which are fastened symmetrically to combustor walls, are situated downstream of the strut injector. To evaluate the performance of the cavity-coupled DLR scramjet model under varying inflow air total temperatures, flow patterns, and flow property distributions are analyzed. The cavity configurations, compared to the baseline model, enhance combustion efficiency by achieving complete combustion while reducing the length of the combustion chamber. However, the introduction of additional shock waves from the cavities results in an increased overall pressure drop. Additionally, as the inflow air total temperature rises, the combustion zone extends further along the flow direction, contributing to a prolonged combustion process.</p>