A high-order spectral difference flow solver is used to perform direct numerical simulations (DNS) of a hypersonic laminar boundary layer on an ultrasonically absorptive coating (UAC), in order to analyze the stabilizing effects of such a material on the laminar–turbulent transition. The UAC is modeled in the simulations by a time-domain impedance boundary condition, which is calibrated to replicate the acoustic response of the UAC over a broad spectral range. The frequency-dependence damping effectiveness is investigated, as are any other side effects the porous coating might have on the mean flow. It is found that the second-mode instability, which dominates the high-Mach number flow regime, is strongly suppressed for all excitation frequencies considered. The DNS solutions are also found to compare favorably with linearized stability theory. Finally, a side effect of the UAC is the modification of the medium dispersive properties and the change of the perturbation group velocity.
Numerical Analysis of Porous Coatings Stabilizing Capabilities on Hypersonic Boundary-Layer Transition
AIAA Journal ; 59 , 10 ; 3845-3858
2021-07-02
14 pages
Article (Journal)
Electronic Resource
English
Acoustic Properties of Porous Coatings for Hypersonic Boundary-Layer Control
Online Contents | 2010
|Acoustic Properties of Porous Coatings for Hypersonic Boundary-Layer Control
British Library Conference Proceedings | 2010
|