A preliminary design study of supersonic through-flow fan inlets

Abstract

For Mach 3.20 cruise propulsion systems, preliminary design studies for two supersonic thrQugh-flow fan primary inlets and a single core inlet were undertaken. Method of characteristics and one-dimensional performance techniques were applied to assess the potential improvements supersonic through-flow fan technology has over more conventional systems. A fixed geometry supersonic through-flow fan primary inlet was found to have better performance than a conventional inlet design on the basis of total pressure recovery, air flow, aerodynamic drags and size and weight. NOMENCLATURE A area BPR bypass ratio C D drag coefficient M Mach number