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Pierre E. Sullivan

Publications and source records attributed to Pierre E. Sullivan.

6 recordsLinked to original sources

GPU-native Embedding of Complex Geometries in Adaptive Octree Grids Applied to the Lattice Boltzmann Method

Adaptive mesh refinement (AMR) reduces computational costs in CFD by concentrating resolution where needed, but efficiently embedding complex, non-aligned geometries on GPUs remains challenging. We present a GPU-native algorithm for incorporating stationary triangle-mesh geometries into block-structured forest-of-octrees grids, performing both solid voxelization and automated near-wall refinement entirely on the device. The method employs local ray casting accelerated by a hierarchy of spatial bins, leveraging efficient grid-block traversal to eliminate the need for index orderings and hash tables commonly used in CPU pipelines, and enabling coalesced memory access without CPU-GPU synchronization. A flattened lookup table of cut-link distances between fluid and solid cells is constructed to support accurate interpolated bounce-back boundary conditions for the lattice Boltzmann method (LBM). We implement this approach as an extension of the AGAL framework for GPU-based AMR and benchmark the geometry module using the Stanford Bunny (112K triangles) and XYZ RGB Dragon (7.2M triangles) models from the Stanford 3D Scanning Repository. The extended solver is validated for external flows past a circular/square cylinder (2D, $Re = 100$), and a sphere (3D, $\text{Re}\in\{10, 15, 20\}$). Results demonstrate that geometry handling and interpolation impose modest overhead while delivering accurate force predictions and stable near-wall resolution on adaptive Cartesian grids. The approach is general and applicable to other explicit solvers requiring GPU-resident geometry embedding.

cs.CE

Characterizing 3D Reattached Flow on an Airfoil with Finite-Span Synthetic Jets

This paper synthesizes prior studies to develop a comprehensive three-dimensional description of reattached flow over an airfoil controlled by finite-span SJA arrays. When applied to a longer-span wing, the flow field exhibits three distinct regions: a directly controlled region, an unaffected region, and a transitional zone between them. Through the integration of multiple visualizations and measurements from both discrete and slot-style SJAs, this work provides insights into the shear layer behavior. The analysis of reattached mean flow provides insight into the interactions between controlled and surrounding flows, demonstrating broad applicability across different SJA configurations

physics.flu-dyn

Towards a GPU-Native Adaptive Mesh Refinement Scheme for the Lattice Boltzmann Method in Complex Geometries

We present a GPU-native mesh adaptation procedure that incorporates a complex geometry represented with a triangle mesh within a primary Cartesian computational grid organized as a forest of octrees. A C++/CUDA program implements the procedure for execution on a single GPU as part of a new module with the AGAL framework, which was originally developed for GPU-native adaptive mesh refinement (AMR) and fluid flow simulation with the Lattice Boltzmann Method (LBM). Traditional LBM is limited to grids with regular prismatic cells with domain boundaries aligned with the cell faces. This work is a first step towards an implementation of the LBM that can simulate flow over irregular surfaces while retaining both adaptation of the mesh and the temporal integration routines entirely on the GPU. Geometries can be inputted as a text file (which generates primitive objects such as circles and spheres) or as an STL file (which can be generated by most 3D modeling software). The procedure is divided into three steps: 1) an import step where the geometry is loaded into either an index list arrangement or directly as a face-vertex coordinates list, 2) a spatial binning step where the faces are distributed to a set of bins with user-defined density, and 3) a near-wall refinement step where the cells of the computational grid detect adjacency to the faces stored in the appropriate bin to form the links between the geometry and the boundary nodes. We validate the implementation and assess its performance in terms of total execution time and speedup relative to a serial CPU implementation using a 2D circle and a 3D Stanford bunny.

cs.CG

Role of Duty Cycle in Burst-Modulated Synthetic Jet Flow Control

The effect of duty cycle (DC) and blowing ratio on synthetic jet flow control over a stalled NACA 0025 airfoil at Re_c=10^5 was investigated experimentally. A finite-span microblower array operating with burst modulation was tested across a wide range of control parameters to assess aerodynamic performance, power consumption, and flow stability. Flow reattachment was achieved once a threshold momentum coefficient was met via increasing either the DC or blowing ratio. Control effectiveness increased sharply upon reattachment, with additional momentum providing incremental improvements in lift, spanwise control, and flow stability, though these effects eventually saturated. Substantial lift improvements are observed at DCs as low as 5%, indicating that brief, high-momentum bursts were the most power-efficient for achieving reattachment. However, flow stability was reduced at low DCs due to the inconsistent streamwise dissipation of spanwise vortices responsible for flow control. Higher DC control strategies resulted in more consistent boundary layer control. These results provide a framework for selecting control strategies that balance aerodynamic performance and stability with power efficiency.

physics.flu-dyn

Spanwise Control Authority of Synthetic Jets on a Stalled Airfoil

This study investigates the aerodynamic effects of low- and high-frequency synthetic jet control strategies on a National Advisory Committee for Aeronautics (NACA) 0025 airfoil. Visualizations and measurements are employed to assess the stability of the flow, focusing on the shear layer and wake dynamics under two forcing frequencies. High-frequency actuation is found to induce steadier flow reattachment and more favorable aerodynamic characteristics compared to low-frequency control. Flow structures resulting from high-frequency actuation, notably vortex rings, are identified and their significance in flow control is evaluated. Furthermore, the spanwise control authority is analyzed, revealing variations in aerodynamic stability away from the midspan. Insights from modal analysis provide additional understanding of flow structures and their evolution across different spanwise planes.

physics.flu-dyn

Visualizing Three-Dimensional Effects of Synthetic Jet Flow Control

This study investigates the three-dimensionality of synthetic jet flow control over a NACA 0025 profile wing using horizontal and vertical smoke wire visualization. The stalled flow in the baseline case is visualized, providing insights into the shear layer roll-up process, the transition to turbulence, and vortex shedding in the wake. In the controlled flow study, two actuation frequencies, $F^+=1.18$ and $F^+=11.76$, are investigated, with a focus on spanwise control authority and the role of coherent structures in flow reattachment. The results indicate that while the control is effective at the midspan over the entire chord length, its effect diminishes with increasing distance from the midspan. Both control cases result in significant spanwise velocities, observed by a contraction of the flow towards midspan. Lastly, the high-frequency actuation results in unique small-scale structures at the shear layer-freestream interface.

physics.flu-dyn