Abstract: Method and apparatus for controlling the aerodynamics of an aircraft using an active flow control system is disclosed herein. In one example, the active flow control system includes an airframe and a plurality of fluidic oscillators. The airframe includes an inlet configured for flight speeds ranging from subsonic to hypersonic. The plurality of fluidic oscillators is mounted about a curvature of the airframe. Each fluidic oscillator includes a body and an integral nozzle coupled to the body. The body has an inflow portion and a narrow nozzle inlet formed opposite the inflow portion. The integral nozzle is coupled to the body by the narrow nozzle inlet. The narrow nozzle inlet forms a single fluid flow path from the inflow portion to the narrow nozzle inlet.

Abstract: Methods and apparatus to model thermal mixing for prediction of multi-stream flows are described. An example method includes determining characteristics of a nozzle of an aircraft; estimating momentum diffusion due to turbulence associated with the nozzle based on the determined characteristics; and estimating thermal diffusion due to the turbulence associated with the nozzle based on the estimated momentum diffusion, wherein the estimating of the thermal diffusion due to the turbulence is based on a spatially varying turbulent Prandtl number.

Abstract: Method and apparatus for controlling the aerodynamics of an aircraft using an active flow control system is disclosed herein. In one example, the active flow control system includes an airframe and a plurality of fluidic oscillators. The airframe includes an inlet configured for flight speeds ranging from subsonic to hypersonic. The plurality of fluidic oscillators is mounted about a curvature of the airframe. Each fluidic oscillator includes a body and an integral nozzle coupled to the body. The body has an inflow portion and a narrow nozzle inlet formed opposite the inflow portion. The integral nozzle is coupled to the body by the narrow nozzle inlet. The narrow nozzle inlet forms a single fluid flow path from the inflow portion to the narrow nozzle inlet.

Abstract: Method and apparatus for controlling the aerodynamics of an aircraft using an active flow control system is disclosed herein. In one example, the active flow control system includes an airframe and a plurality of fluidic oscillators. The airframe includes an inlet configured for flight speeds ranging from subsonic to hypersonic. The plurality of fluidic oscillators is mounted about a curvature of the airframe. Each fluidic oscillator includes a body and an integral nozzle coupled to the body. The body has an inflow portion and a narrow nozzle inlet formed opposite the inflow portion. The integral nozzle is coupled to the body by the narrow nozzle inlet. The narrow nozzle inlet forms a single fluid flow path from the inflow portion to the narrow nozzle inlet.

Abstract: Methods and apparatus to model thermal mixing for prediction of multi-stream flows are described. An example method includes determining characteristics of a nozzle of an aircraft; estimating momentum diffusion due to turbulence associated with the nozzle based on the determined characteristics; and estimating thermal diffusion due to the turbulence associated with the nozzle based on the estimated momentum diffusion, wherein the estimating of the thermal diffusion due to the turbulence is based on a spatially varying turbulent Prandtl number.

Abstract: A method for dynamic load balancing of a mesh, wherein the mesh is partitioned to find a solution using a plurality of processors, and wherein the partitions have become unbalanced. The present method allows large portions of the mesh to continue to progress towards a solution by only repartitioning a small percentage of the overall mesh. This is done by stripping cells along the partition interfaces using a marching method to form a free-cell region, repartitioning the free-cell region, and joining the repartitioned portions of the free-cell region with the remaining cells in a manner that will increase the efficiency of the solver.

Abstract: A method for dynamic repartitioning of a mesh, wherein the mesh is partitioned to find a solution using a plurality of processors, and wherein the partitions have become unbalanced. The present method allows large portions of the mesh to continue to progress towards a solution by only repartitioning a small percentage of the overall mesh. This is done by stripping cells along the partition interfaces using a marching method to form a free-cell region, repartitioning the free-cell region, and joining the repartitioned portions of the free-cell region with the remaining cells in a manner that will increase the efficiency of the solver.