Direct numerical simulations on the receptivity of hypersonic boundary layers over a flat plate and a sharp wedge were carried out with two-dimensional periodic-in-time wall blowing-suction introduced into the flow through a slot. The freestream Mach numbers were equal to 5.92 and 8 in the cases of the adiabatic flat plate and sharp wedge, respectively. The perturbation flowfield was decomposed into normal modes with the help of the multimode decomposition technique based on the spatial biorthogonal eigenfunction system. The decomposition allowed for the filtering out of stable and unstable modes hidden behind perturbations of another physical nature.
ASJC Scopus subject areas
- Aerospace Engineering