Cascade Wind Tunnel for Transonic Compressor Blading Studies.
NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
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The design and construction of a small, transonic, cascade wind tunnel are reported. The tunnel is of the intermittent blow-down type, and the initial test cascade models the flow at the rotor blade tips of a single stage transonic compressor at a relative Mach number of 1.4. General programs were developed for the design of round-to-rectangular transition sections and for the computation of supersonic nozzle contours. Complete machine drawings for the important components of the facility are included. Author
- Hydraulic and Pneumatic Equipment
- Test Facilities, Equipment and Methods
- Fluid Mechanics