Instrumentation for Investigating Precursors to High Reynolds Number Unsteady Flow Separation on Pitching Airfoils.
Abstract
A pitching airfoil test facility has been developed to enable investigating the unsteady flow separation process on helicopter rotor blades under flow conditions which replicate the viscous-inviscid interactions. The facility is capable of operating at chord based Reynolds numbers of 106 and reduced frequencies of 0.23 while maintaining the Mach number below 0.15. A multi-element compliant wall sensor has been developed to measure pressure fluctuations just preceding the emption of the boundary layer. Following successful implementation on cylinders and non-pitching airfoils, this transducer has been used to detect the propagation of wall pressure fluctuations in the neighborhood of the separation point. Preliminary data obtained by sampling simultaneously the data from eight transducer strips has revealed patterns characteristic to the boundary layer emption process.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 10, 1996
- Accession Number
- ADA316875
Entities
People
- Chuck Baker
- Debjyoti Banerjee
- Dipankar Pal
- Mukesh Pandey
- Sumon K. Sinha
Organizations
- University of Mississippi