Numerical and experimental studies have demonstrated laminar–turbulent transition in
hypersonic boundary layers over sharp cones via the modal growth of planar Mack-mode …

The existing database of transition measurements in hypersonic ground facilities has
established that, as the nose-tip bluntness is increased, the onset of boundary-layer …

Time-resolved surface temperature measurements have been carried out on a 7° half-angle
circular cone/flare model in the Air Force Research Laboratory's Mach-6 Ludwieg Tube …

The boundary-layer receptivity of the second mode to a slow acoustic wave is investigated
using direct numerical simulation for a Mach 6 flow over a blunt cone with the nose radius of …

View Video Presentation: https://doi. org/10.2514/6.2022-3250. vid The existing
measurements of laminar-to-turbulent transition over circular cones in conventional (ie," …

The fundamental understanding of the Sanal flow choking and/or sonic fluid throat effect
(VRS Kumar et al., Physics of Fluids, 34 (4 & 10), 2022) in real-world fluid flow system sheds …

Aero-thermal analysis of hypersonic vehicles is of fundamental interest for structural design
and material selection. Therefore, we investigated the aerodynamic heating characteristics …

The effects of nose bluntness on the entropy-layer stabilities in hypersonic flows over blunt
cones and wedges are investigated by using linear stability theory and numerical simulation …

T= temperature [K] Tw= wall temperature [K] Tw, ad= adiabatic wall temperature [K](u, v, w)=
streamwise, wall-normal, and azimuthal velocity components [m· s− 1](x, y, z)= Cartesian …

Direct numerical simulation with up to 10× 10 9 scale grid points based on graphics
processing unit computation is carried out to investigate the bluntness effect on the …