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- Publisher
- Springer Journals
- Copyright
- 2009 The Chinese Society of Theoretical and Applied Mechanics and Springer-Verlag GmbH
- ISSN
- 0567-7718
- eISSN
- 1614-3116
- DOI
- 10.1007/s10409-009-0228-8
- Publisher site
- See Article on Publisher Site
Abstract
Abstract Experimental study was conducted for boundary-layers on a sharp 5° half-angle cone of 400 mm length at angles of attack. The model was tested in the T-326 hypersonic wind tunnel (ITAM) at freestream Mach number M = 5.95. Mean and fluctuation wall characteristics of the boundary layer are measured at 0°, 2°, 3° and 4° angles of attack for different stagnation pressures. Pulsation measurements are carried out by means of ALTP sensor. Pressure and temperature distributions along the model are obtained, and transition beginning and end locations have been found. Boundary layer stabilization with the increase of angle of attack and the decrease of stagnation pressure is observed. High frequency pulsations inherent to hypersonic boundary layer (second mode) have been detected.
Journal
"Acta Mechanica Sinica" – Springer Journals
Published: Jun 1, 2009