The shock wave/boundary-layer interaction is a common phenomenon, and it occurs in the
internal and external flow fields of the hypersonic vehicle. Then, the separation, the …

Adaptive control of flow separation based on online dynamic mode decomposition (DMD) is
formulated and implemented on a canonical separated laminar boundary layer via a pulse …

Shock wave/turbulent boundary layer interactions under the effect of a transverse jet at
different distances are investigated via large eddy simulation. The instantaneous …

Methods for adaptive control of flow separation based on dynamic mode decomposition
(DMD) are formulated and implemented on a canonical separated flow subjected to …

Suppressing shock-induced flow separation has been a long-standing problem in the
design of supersonic vehicles. To reduce the structural and design complexity of control …

This study examines boundary layer control and pressure recovery in low Reynolds number
supersonic flow with chemical reactions in a chemical laser system. Our work prescribes a …

We conduct numerical flow control studies on a NACA4412 wing. Direct numerical
simulation of laminar separated flows is conducted in the Nek5000 spectral element code …

Numerical flow control studies are conducted on a NACA 0015 airfoil and finite wing of
aspect ratio 4 at a chord based Reynolds number of 200 and high angles of attack. Direct …

Aircraft, turbomachinery, wind turbines, and other systems that generate or rely on
aerodynamic forces are designed to operate most efficiently when flows are fully attached …

An experimental study is done to check the influence of multi-layered piezoceramic actuator
at the throat and downstream of transonic diffuser. The diffuser has circular arc upper wall …