An active flow control application on a realistic wing design could be leveraged by a scalable, fully implicit, unstructured, finite-element flow solver and high-performance computing resources. This article describes the active flow control application; summarizes the main features in the implementation of a massively parallel turbulent flow solver, PHASTA; and demonstrates the method's strong scalability at extreme scale.

Summary. This paper describes a parallel procedure for anisotropic mesh adaptation with boundary layers for use in scalable CFD simulations. The parallel mesh adaptation algorithm operates with local mesh modification operations developed for both unstructured and boundary layer parts of the mesh. The adaptive approach maintains layered elements near the viscous walls and accounts for the mesh modification operations that are carried out in parallel on a distributed mesh. In the process mesh relationships and approximations with respect to curved complex 3D geometries of interest are properly maintained. The parallel mesh adaptation procedures are applied to two problems: a heat transfer manifold and a scramjet engine.

No abstract

Simulation of wall-bounded turbulent flows poses significant challenges and requires tightly controlled mesh spacing and structure near the walls. Semi-structured or hybrid meshes are often used for turbulent boundary layer flows. These meshes not only account for complex geometry but also maintain highly anisotropic, graded and layered elements near the walls. However, for engineering flow problems the mesh spacing required to achieve a given level of accuracy cannot be determined a priori and therefore, an adaptive approach becomes essential. For wall-bounded turbulent flows, such an approach must incorporate the structure of the turbulent boundary layer and associated flow physics in order to guide the adaptive process. This paper introduces a new approach for boundary layer adaptivity, wherein flow physics indicators are used in combination with interpolation-based or numerical error indicators. The effectiveness of the current technique is demonstrated by applying them to two aerodynamic