We perform a resolvent analysis to examine the perturbation dynamics over the laminar
separation bubble (LSB) that forms near the leading edge of a NACA 0012 airfoil at a chord …

This study investigates the flow evolution past a pitching NACA0012 airfoil undergoing deep
dynamic stall using a wall-resolved large eddy simulation approach. Numerical results are …

This study investigates a mechanism for controlling separated flows around an airfoil using a
synthetic jet (SJ). A large-eddy simulation (LES) was performed for a leading-edge …

Large-eddy simulations of the onset of dynamic stall for a NACA 0012 airfoil, pitching at a
constant rate, are performed for a chord Reynolds number of 1.0× 1 0 6. Using four …

This study numerically investigated the mechanisms of separation control using a synthetic
jet (SJ) and plasma actuator (PA) around an NACA0015 airfoil at the chord Reynolds …

Large-eddy simulations (LES) are employed to investigate the pitch–plunge equivalence of
an SD7003 airfoil undergoing constant ramp motions at Reynolds number R e= 6× 10 4. The …

Pitch/plunge equivalence for deep dynamic stall of a straight finite wing is considered by
employing large-eddy simulations. The flowfields are computed with a well-established time …

The onset of dynamic stall limits the maximum airspeed of helicopters. For Reynolds
numbers where laminar separation precedes transition, the bursting of a leading edge …

Large-eddy simulations of dynamic stall for a wing section with NACA0012 airfoil were
performed for three cases from the literature: A case modeled after Gupta and Ansell [AIAA …

A high-fidelity numerical study is undertaken to expand the notion of pitch/plunge
equivalence to finite, swept wings undergoing deep-dynamic stall and builds upon the …