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.


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