On the simulation of a wing with detached end-plates using an actuator line based on an anisotropic Gaussian kernel

The results of an actuator line method (ALM) using an anisotropic Gaussian kernel for both, velocity sampling and force projection, are compared to the wall-resolved results of a NACA 0015 rectangular wing at an angle of attack of 10°. The rectangular wing is simulated both, with and without, detached end-plates to show that the ALM is capable of accounting for the presence of a narrow gap of 0.01 c between the tip of the wing and the end-plate. The anisotropic kernel shape is varied in the chordwise, thickness-wise, and spanwise directions for different grid sizes and number of actuating points. The body forces are truncated and regularized to enforce proper spacing between the actuating line and the end-plate. ALM and wall-resolved results are compared on the basis of the integrated lift and drag coefficients, the sectional lift and drag coefficients, as well as the tip vortex core size, position, and circulation. Recommendations are made regarding the optimal kernel shape for a given number of actuating points and mesh resolution.