Boundary layer transition measurements in hypervelocity flows in a shock tunnel

Mee, D. J. (2001). Boundary layer transition measurements in hypervelocity flows in a shock tunnel. In: 39th AIAA Aerospace Sciences Meeting and Exhibit. 39th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, USA, (1-11). 8-11 January, 2001. doi:10.2514/2.1851


Author Mee, D. J.
Title of paper Boundary layer transition measurements in hypervelocity flows in a shock tunnel
Conference name 39th AIAA Aerospace Sciences Meeting and Exhibit
Conference location Reno, Nevada, USA
Conference dates 8-11 January, 2001
Proceedings title 39th AIAA Aerospace Sciences Meeting and Exhibit   Check publisher's open access policy
Journal name 39th Aerospace Sciences Meeting and Exhibit   Check publisher's open access policy
Place of Publication USA
Publisher American Institute of Aeronautics and Astronautics
Publication Year 2001
Year available 2002
Sub-type Fully published paper
DOI 10.2514/2.1851
Open Access Status Not yet assessed
ISSN 0001-1452
Volume 40
Issue 2001-0208
Start page 1
End page 11
Total pages 11
Language eng
Abstract/Summary Experiments to investigate the transition process in hypervelocity boundary layers were performed in the T4 free-piston shock tunnel. An array of thin-film heat-transfer gauges was used to detect the location and extent of the transitional region on a 1500 mm long x 120 turn wide flat plate, which formed one of the walls of a duct. The experiments were performed in a Mach 6 flow of air with 6- and 12-MJ/kg nozzle-supply enthalpies at unit Reynolds numbers ranging from 1.6 x 10(6) to 4.9 x 10(6) m(-1). The results show that the characteristics typical of transition taking place through the initiation, growth, and merger of turbulent spots are evident in the heat-transfer signals. A 2-mm-high excrescence located 440 turn from the leading edge was found to be capable of generating a turbulent wedge within an otherwise laminar boundary layer at a unit Reynolds number of 2.6 x 10(6) m(-1) at the 6-MJ/kg condition. A tripping strip, located 100 mm from the leading edge and consisting of a line 37 teeth of 2 rum height equally spaced and spanning the test surface, was also found to be capable of advancing the transition location at the same condition and at the higher enthalpy condition.
Subjects EX
290299 Aerospace Engineering not elsewhere classified
780102 Physical sciences
Keyword Turbulent Spots
Stability
Q-Index Code EX
Institutional Status UQ

Document type: Conference Paper
Sub-type: Aiaa Journal
Collection: School of Mechanical & Mining Engineering Publications
 
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Created: Fri, 24 Aug 2007, 10:15:51 EST