Cascade wind tunnel for transonic compressor blading studies.

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.U-. General programs were developed for the design of round-torectangular transition sections and for the computation of supersonic nozzle contours. Complete machine drawings for the important components of the facility are included.

Department dc:contributor.department

Mechanical Engineering

Year dc:date.issued

1978

Author dc:creator

• Demo, Willard Joe

Advisor dc:contributor.advisor

• Shreeve, R.P.

Statement dc:rights

• This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.

Language dc:language.iso

en_US

Handle dc:identifier.uri

https://hdl.handle.net/10945/18365

OAI identifier oai:identifier

oai:calhoun.nps.edu:10945/18365