The laminar basic flow of a hypersonic blunt cone boundary layer with zero angle of attack,at oncoming Mach number 6,was calculated firstly,and then,a group of T-S wave disturbances with finite amplitude was introduced at the entrance of the computational domain selected,the direct numerical simulation(DNS) was performed with high order difference scheme being employed.

Analysis of dynamic images based on wavelet transform in a hypersonic boundary layer

The perturbation phenomena in hypersonic flat plate boundary layer are investigated wi th electronic beam fluorescence technique in a gun wind tunnel.

Several fundamental research topics are discussed for future research,which in- clude the advanced hypersonic test facilities;modeling aero-thermo-chemistry;stagnation flow region prediction; hypersonic boundary layer transition and shock waves/viscous interactions.

A numerical study for the generation of shocklet by 3-D disturbances in supersonic boundary layer;

A study of the boundary condition in the DNS of the supersonic boundary layer flow;

The spatial evolution of 2-D disturbances in supersonic sharp cone boundary layers was investigated by direct numerical simulation(DNS) in high order compact difference scheme.