Numerical simulation of a delta wing at high angles of attack

Low speed flows around a delta wing body at high angles of attack were simulated by using the flow solver FINE^TM/HEXA which is based on all-hexahedral unstructured mesh. Simulation results show good agreement with the experimental data. The convergence is greatly accelerated with the method of agglomeration, and 3D mesh adaptation can help to capture the delicate flow features while the mesh cell number remains not very large in global. This paper also presents analysis of the flow features ahead and behind of the leading edge vortex breakdown and the topological features of section streamlines.