The increased need for efficient supersonic flight has revived interest in supersonic throughflow fans for advanced high-speed propulsion systems. NASA LeRC recently began a program to design, build, and test a single-stage fan that will operate with supersonic air velocity sustained through the blade rows. In a major revamping of the LeRC Multistage Compressor Facility, NASA has built a 20 in. diameter annular wind tunnel with a 0.7 hub-to-tip ratio. The wind tunnel houses a high-speed rotating fan package. The objectives of this research program are to demonstrate feasibility, to gain an understanding of the flow physics, and to create a data base. The facility, test package, and instrumentation for supporting the operation of the supersonic throughflow fan program are described.
Supersonic Throughflow Fan Test Facility at NASA. Lewis Research Center
1990
25 pages
Report
No indication
English
Aircraft , Aerodynamics , Test Facilities & Equipment , Jet & Gas Turbine Engines , Propulsion system configurations , Propulsion system performance , Supersonic flow , Supersonic test apparatus , Supersonic turbines , Supersonic wind tunnels , Turbofans , Supersonic speed , Wind tunnel drives , Data bases , Engine tests , Supersonic combustion , Supersonic compressors , Supersonic transports , Turbocompressors