Hypersonic Wind-Tunnel Measurements of Boundary-Layer Pressure Fluctuations
Abstract
During atmospheric reentry, hypersonic vehicles are subjected to high levels of boundary-layer pressure fluctuations. To improve understanding and prediction of these fluctuations, measurements of surface pressure fluctuations on a seven-degree sharp cone at zero angle of attack were conducted in Sandia's Hypersonic Wind Tunnel under noisy flow and in Purdue University's Boeing/AFOSR Mach-6 Quiet Tunnel under noisy and quiet flow. Fluctuations under laminar boundary layers reflected tunnel noise levels. Laminar boundary-layer measurements under quiet flow were an order of magnitude lower than under noisy flow. Transition on the model only occurred under noisy flow, and fluctuations peaked during transition. The transition location, marked by the peak, depended on tunnel noise parameters.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 2009
- Accession Number
- ADA504177
Entities
People
- Katya M. Casper
Organizations
- Purdue University