Simulation of aeroelastic mesoflaps for shock/boundary-layer interaction

A novel concept involving an array of mesoflaps that allow for aeroelastic recirculating transpiration has the capability to control shock/boundary-layer interactions. The concept consists of a matrix of small flaps (rigidly fixed at their upstream end and covering an enclosed cavity) which are designed to undergo aeroelastic deflection to achieve proper mass bleed or injection when subjected to gas dynamic shock loads. To investigate the static behavior of the mesoflap system, a loosely coupled aeroelastic finite element scheme was developed. The technique uses an unstructured grid for both the fluid and solid domains to allow for potentially complex geometries. Issues of optimum fluid cycles per aeroelastic iteration, under-relaxation, and adaptive mesh re-gridding versus motion were considered in the context of the flap deflection. The aeroelastic convergence was accelerated and improved by employing such techniques.