Compressible Turbulence Measurements in a Supersonic Boundary Layer with Impinging Shock Wave Interaction
Abstract
This study used laser Doppler velocimetry techniques to measure the turbulence intensities and Reynolds shear stresses in a Mach 2.9 turbulent flat plate with an impinging shock wave. The shock strength was varied, using three wedge shock generators with turning angles of 50, 70, and 100. Each flow field was studied at four locations, X = %1.326o, 06o, 1.326o, 2.64%, relative to the shock wave/boundary layer interaction. An additional streamwise profile, parallel to the wall at a height of = 0.66. This study showed that the velocity fluctuations (%, %) were energized by the shock wave/boundary layer interaction, and while remaining at a higher value than the upstream stations, decreased in value with distance downstream of the interaction. The Reynolds shear stress -%pu'v' followed a similar pattern, sharply increasing immediately after the interaction and dissipating with distance downstream of the interaction.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1996
- Accession Number
- ADA308529
Entities
People
- Michael J. Meyer
Organizations
- Air Force Institute of Technology