This study investigates a modified scramjet design, termed the forward strut model, based on the DLR scramjet, where two smaller struts are positioned ahead of the main strut. Numerical simulations using the density-based SST k-ω turbulence model at supersonic Mach numbers, with hydrogen as the fuel, were conducted to assess the effects of this design on combustion and fuel–air mixing efficiencies. The forward strut model demonstrated a 3.9% improvement in combustion efficiency, reaching 63.9% compared to 60% in the baseline model. Additionally, it achieved complete fuel–air mixing 20 mm earlier, with full mixing at 260 mm compared to 280 mm in the baseline model, which showed 96% efficiency at that location. These findings suggest that the forward strut configuration enhances fuel–air interaction, improves combustion efficiency, and offers valuable insights for optimizing scramjet performance at supersonic speeds, contributing to advancements in high-speed aerospace propulsion.