Discrete vortex-based broadcast mode analysis for mitigation of dynamic stall

TL;DR

This paper combines discrete vortex modeling with network analysis to optimize flow control strategies, effectively reducing dynamic stall effects on airfoils through targeted actuator placement and timing.

Contribution

It introduces a novel framework integrating vortex-based flow modeling with network broadcast mode analysis for dynamic stall mitigation.

Findings

Optimal disturbance timing is just after separation onset.

Actuators placed near the leading edge improve control effectiveness.

Flow control reduces peak lift by up to 30%.

Abstract

We integrate a discrete vortex method with complex network analysis to strategize dynamic stall mitigation over a pitching airfoil with active flow control. The objective is to inform actuator placement and timing to introduce control inputs during the transient evolution of dynamic stall. To this end, we represent the massively separated flow as a network of discrete vortical elements and quantify the interactions among these vortical nodes by tracking the spread of displacement perturbations between each pair of elements using the discrete vortex method. This enables a network broadcast mode analysis to identify an optimal set of vortices, critical timing, and direction to seed perturbations as control inputs. Motivated by the goal of mitigating dynamic stall, the optimality is defined as minimizing the total circulation of free vortices generated from the leading edge over a prescribed time horizon. We demonstrate the framework on two cases: two-dimensional flow over a flat plate airfoil and three-dimensional turbulent flow over a SD7003 airfoil. The analysis reveals that optimal timing for introducing disturbances occurs just after separation onset, when the shear layer pinches up to form the core of the dynamic stall vortex. Broadcast modes indicate that vortical nodes along the shear layer are optimal for control, guiding actuator placement. Flow simulations validate these insights: placing actuators near the leading edge and triggering them shortly after separation yields a 12% and 30% reduction in peak lift for the flat plate and SD7003 cases, respectively. A corresponding decrease in vorticity injection under control confirms the analysis objective. This study highlights the potential of combining discrete vortex methods with network analysis to guide active flow control in unsteady aerodynamics.