Analytical method of prediction of turbulent boundary-layer separation in hypersonic flows

Dann, Andrew G. and Morgan, Richard G. (2011) Analytical method of prediction of turbulent boundary-layer separation in hypersonic flows. AIAA Journal, 49 9: 2068-2072.


Author Dann, Andrew G.
Morgan, Richard G.
Title Analytical method of prediction of turbulent boundary-layer separation in hypersonic flows
Journal name AIAA Journal   Check publisher's open access policy
ISSN 0001-1452
1533-385X
Publication date 2011-09
Sub-type Article (original research)
DOI 10.2514/1.J050673
Volume 49
Issue 9
Start page 2068
End page 2072
Total pages 5
Place of publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics
Collection year 2012
Language eng
Abstract An analytical method of prediction of turbulent boundary-layer separation in hypersonic flows is presented. The boundary layer is associated with a flat plate for simplicity and is recognized as a fully turbulent boundary layer with a sufficiently high Reynolds number. A separated boundary layer has recirculating flow. The moment of separation can be more easily visualized by looking at velocity profiles within the boundary layer as it is subjected to greater pressure gradients. The velocity gradient at the wall will be zero, and the momentum flux out of the control volume will be approaching zero at the point of incipient separation. The shear stress at the wall cannot be estimated using the seventh power law, since it is not valid in the laminar sublayer. A possible reason for the independence on Reynolds number could be the assumption that the distance over which separation occurs is short and the shear stress can therefore be neglected.
Keyword Elliptic shape transition
Supersonic-flow
Q-Index Code C1
Q-Index Status Confirmed Code
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2012 Collection
 
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