Experimental Determination of Turning Angle and Losses of Axial Compressor Inlet Guide Vanes.
Abstract
The investigation experimentally determined the minimum loss incidence angle, deviation angle, and total-pressure loss coefficient for a cascade with airfoil-type blade profiles used as inlet guide vanes for an axial-flow compressor with an equivalent camber angle of 37.6 degrees and unit solidity. The experimental values were compared with values predicted using correlations based on compressor cascade tests. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1972
- Accession Number
- AD0757250
Entities
People
- William Richard Wheeler
Organizations
- Naval Postgraduate School