Volume 5, Juin 2013Progress in Flight Physics
|Page(s)||57 - 68|
|Section||Chapter Two. Boundary layer stability|
|Published online||14 June 2013|
Direct numerical simulations of mack-mode damping on porous coated cones
DLR Institute of Aerodynamics and Flow Technology 7 Lilienthalplatz, Braunschweig 38108, Germany
The flow field over a 3 degree blunt cone is investigated with respect to a hypersonic stability analysis of the boundary-layer flow at Mach 6 with porous as well as smooth walls by comparing local direct numerical simulations (DNS) and linear stability theory (LST) data. The original boundary-layer profile is generated by a finite volume solver, using shock capturing techniques to generate an axisymmetric flow field. Local boundary-layer profiles are extracted from this flow field and hypersonic Mack-modes are superimposed for cone-walls with and without a porous surface used as a passive transition-reduction device. Special care is taken of curvature effects of the wall on the mode development over smooth and porous walls.
© Owned by the authors, published by EDP Sciences, 2013
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 2.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.