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 …

In the author's previous work, we introduced an open-source accelerated computational fluid
dynamics code for scientific computations using a graphics processing unit system …

View Video Presentation: https://doi. org/10.2514/6.2023-0269. vid This study explores the
evolution of a Mach 8 boundary layer over a spanwise finite expansion-compression …

This paper presents the results of implicit large eddy simulation (iLES) and direct numerical
simulation (DNS) for flow and acoustics for transitional and turbulent boundary layer over a …

The size of a pressure transducer is known to affect the accuracy of measurements of wall-
pressure fluctuations beneath a turbulent boundary layer because of spatial averaging over …

View Video Presentation: https://doi. org/10.2514/6.2022-0056. vid Four Direct Numerical
Simulation (DNS) datasets covering effective freestream Mach numbers of 8 through 14 are …

This paper presents a study of high speed boundary layers using the wavelet method. We
analyze direct numerical simulation data for highspeed, compressible transitional, and …

View Video Presentation: https://doi. org/10.2514/6.2021-2832. vid The character of aero-
optical distortions produced by turbulence is investigated for subsonic, supersonic, and …

Wall pressure fluctuations beneath a boundary layer are the main cause of structural
vibration for hypersonic aircraft. To accurately predict the load environment of pressure …

Laminar-to-turbulent transition in hypersonic boundary layer is numerically investigated
using the direct-numerical simulation (DNS) method combined with the linear stability theory …