Experiments are performed in a Mach-6 shock tunnel to examine the laminar-to-turbulent
transition process associated with a sudden increase in surface angle on a slender body. A …

A nonlinear ensemble-variational data assimilation is performed in order to estimate the
unknown flow field over a slender cone at Mach 6, from isolated wall-pressure …

Unsteady surface pressure measurements have been carried out on a flat-plate test article in
the Air Force Research Laboratory's Mach-6 Ludwieg Tube at a negative angle of attack …

View Video Presentation: https://doi. org/10.2514/6.2023-2438. vid A self-aligned focusing
schlieren (SAFS) apparatus based on a recently published design is implemented for the …

The present paper finds that the coexistence of multiple primary instability waves may cause
a non-trivial nonlinear interaction and breakdown process, which has not been reported …

View Video Presentation: https://doi. org/10.2514/6.2022-3530. vid The state of the boundary
layer at high Mach numbers has significant influence on the wall shear stress and thus wall …

Computational investigations of a tangent ogive-cylinder geometry with varying forebodies
at zero degrees angle of attack are presented. The model geometry and conditions are …

The interaction between the hypersonic flow over a cone and a side jet creates complex
multiple recirculation regions as well as separation, reattachment, and bow shocks known …

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," …

View Video Presentation: https://doi. org/10.2514/6.2023-0869. vid The reconstruction of
globally-consistent hypersonic boundary layer disturbance modes from experimental …