A preliminary design study of supersonic through-flow fan inletsFrom Mach 3.20 cruise propulsion systems, preliminary design studies for two supersonic through-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 drag and size and weight.
Document ID
19880065910
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Barnhart, Paul J. (NASA Lewis Research Center Cleveland; Sverdrup Technology, Inc., Middleburg Heights, OH, United States)