Abstract
We present simulations of turbulent detached flows using the commercial lattice Boltzmann solver XFlow (by Dassault Systemes). XFlow’s lattice Boltzmann formulation together with an efficient octree mesh generator reduce substantially the cost of generating complex meshes for industrial flows. In this work, we challenge these meshes and quantify the accuracy of the solver for detached turbulent flows. The good performance of XFlow when combined with a Large-Eddy Simulation turbulence model is demonstrated for different industrial benchmarks and validated using experimental data or fine numerical simulations. We select five test cases: the Backward-facing step the Goldschmied Body the HLPW-2 (2nd High-Lift Prediction Workshop) full aircraft geometry, a NACA0012 under dynamic stall conditions and a parametric study of leading edge tubercles to improve stall behavior on a 3D wing.
Highlights
Aerodynamic performance plays a major role in the design process of an aircraft
The lift coefficient predicted at 16 deg by XFlow shows a relative error of only 0.7% when compared to wind-tunnel data, and the linear slope is exactly matched
We observe that the track fairings and the pressure tube bundles have a negligible effect on the aerodynamics, in the linear region
Summary
Aerodynamic performance plays a major role in the design process of an aircraft. The aeronautical industry has been using Computation Fluid Dynamics (CFD) as a complement to wind tunnel measurements, which are typically executed at the end of the production cycle. The flow is laminar when the Reynolds number is Re D < 400 and it can be assumed to be a two-dimensional problem Under these conditions a recirculation zone appears where a strong mixing process takes place. This section contains part of the results published by Holman et al [6] with the most complex geometry They focused on the linear region of lift, drag and moments curves, and pressure coefficient distributions. Massive and abrupt stall, linked to a sudden loss of lift, occurs once the vortex convects at the trailing edge This phenomenon was widely studied experimentally and numerically due to its appearance in helicopters aerodynamics and wind turbines [16,47,48,49].
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