Test of a Supersonic Compressor Cascade. Volume II.
Abstract
The report describes in detail the experimental investigation of a stationary, linear, supersonic compressor blade cascade. The cascade incorporated contoured sidewalls to control the change in stream-tube area in the quasi-axial direction. The blades had a constant spanwise geometry. The selected blade element was from a recent compressor configuration resulting from the Aerospace Research Laboratories supersonic axial compressor research program. The investigation covered a range of inlet relative Mach numbers of 1.40 - 1.50 and a range of static pressure ratios of approximately 1.5 - 2.1. Volume I describes the cascade design, instrumentation, data reduction techniques, test results, and correlation of results with design characteristics. Volume 2 describes additional work with vortex generators mounted on the blades and compares these results with the plain blade results. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1972
- Accession Number
- AD0756871
Entities
People
- G. David Huffman
- George T. Sinnet
- Robert B. Mcclure
- Robert L. Holtman
Organizations
- General Motors