Design and Investigation of Busemann Intakes for High-Speed Propulsion Systems

Axisymmetric Busemann intakes are able to perform internal compression of the incoming supersonic/hypersonic flow minimizing total pressure losses, while the circular cross section and the axial flow uniformity achieved at the exit makes this intake suitable for combustors and nozzles of supersonic/hypersonic vehicles. Although its geometry does not include moving parts, the flow physics is complex and needs to be fully understood in order to meet the desired inflow characteristics for combustion chambers of ramjet/scramjet engines. Moreover, as the viscous effects and leading edge truncation yield various challenging factors regarding the growth of the boundary layers, estimation and control of these features requires extensive analysis to ensure compatibility with the operational and design conditions. Thus, a numerical investigation on Busemann ıntakes is conducted, considering different flight and design conditions. Furthermore, an alternative truncation methodology is also proposed, taking into account the compatibility of flow structures within the contours of the Busemann intake. Accordingly, a comparative assessment of the flow quality is performed with respect to the conventional truncation method.