Hypersonic vehicles employing scramjet engines have gathered great interest from researchers all over the world. Additionally, hydrogen due to its emission free end use is being adopted as a fuel by many industries. Multi-strut injection is a method designed to enhance scramjet performance and decrease the likelihood of supersonic combustor being thermally choked. This research article presents computational investigation of a scramjet engine at Mach 2, utilizing multiple-lobed struts placed centrally, to explore this approach. Two-dimensional steady Reynolds Averaged Navier–Stokes equations are solved numerically using the SST − ω turbulence model. The combustor examined here demonstrates improvements similar to those observed with the configuration tested at the German Aerospace Center (DLR). Struts are positioned parallel to the flow direction to prevent significant issues with fuel injection. The adopted numerical methodology is validated quantitatively and qualitatively with respect to the experimental results. The significant flow features like shock-I and shock-II are captured clearly along with the recirculation zone formed at the base of the strut which facilitate in stabilizing the flame during combustion. The highest static pressure peak along the lower wall for the case of three-strut configuration corresponds to p ≈ 145 kPa, whereas for the case of single strut, it is found to be p ≈ 7.95 kPa. The three-strut combustor configuration shows better turbulent mixing thus, improved combustion performance as compared to the single-strut geometry.