A design of a hypersonic inlet with the purpose of creating high fuel-air mixing efficiency has been modelled and simulated using Reynolds Averaged Navier-Stokes (RANS) computational fluid dynamics (CFD) tools based on the SCRAMSPACE I base geometry and flight conditions. The inlet was modelled with delta-wing-shaped chevrons at the leading edge in order to produce a flow field of counter-rotating vortices formed from separating shear layers that would dominate the flow stream and aide in the mixing efficiency. Two alternate designs were modelled, one with no angle of attack to the incoming flow as a comparison for the second whose chevrons are angled by having an ‘inward-facing’ inlet. Each of these designs had a chevron and no-chevron case. The simulation for the inwardfacing geometry with a chevron successfully solved. The other models did not. By comparing the results with literature and hypersonic theory, the flow path generated by the simulation was identical to a no-chevron case; the chevron did not produce any indication of vortical formation. The flow structure could be easily described by the incident shock formed at the leading edge which dominates the incoming flow. It was expected that this model would have the most success in creating vortices. From previous literature, chevrons have been successful in aiding the mixing efficiency in hypersonic flow. Therefore, it is recommended that more models need to be simulated with different chevron geometry to complete this study. Further study recommendations include optimising the chevrons with respect to sweepback angle, angle of attack, slenderness, sharpness, and number of chevrons. Furthermore, non-obtrusive fuel injection should be introduced to measure the effectiveness of the inlet design.