A Cascade in Unsteady Flow.
Abstract
The flow velocity in an axial compressor, with a distorted inlet pressure profile or rotating stall cells, is unsteady in both magnitude and direction with the unsteadiness in direction having a more abrupt effect on airfoil performance. The objective of this research was to obtain pressure distributions and pressure histories on both surfaces on an airfoil in a cascade while its is undergoing a sinusoidal variation in angle of attack.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1976
- Accession Number
- ADA045319
Entities
People
- Francis R. Ostdiek
Organizations
- Air Force Research Laboratory