Streamwise Vortex Instability and Hypersonic Boundary-Layer Transition on the Hyper-2000
Abstract
Despite the closely coupled nature of hypersonic airbreathing vehicles, the boundary layer transition mechanisms on the forebody ahead of the scramjet inlet are not well understood. Transition induced by the growth of streamwise vortices is studied on a scramjet forebody geometry similar to the Hyper-X. Flow visualization methods are developed in Purdue's Boeing/AFOSR Mach-6 Quiet Tunnel. Fluorescent oil-flow visualization is used to complement instability measurements obtained with temperature-sensitive-paints. The separation zone near the first compression corner is visualized with oil-flow experiments. These experiments also reveal the presence of regularly spaced streamwise vortices on the compression ramp even in the absence of controlled disturbance generators. The growth and decay of these vortices are inferred from heat-transfer measurements using temperature-sensitive paints. Repeatable vortices are generated by wrapping tapes around the leading edge.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 2003
- Accession Number
- ADA417145
Entities
People
- Shin Matsumura
Organizations
- Purdue University