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This paper details the results of ongoing efforts to Improve upon the meshing techniques requIred to produce accurate RANS CFD solutions for attached and separated flows for a Circulation Control aircraft. Work, thus far, under the current NASA Research An nouncemant (NRA) project has revolved around an unstructured near-body volume mesh due to Its robustness for complicated geometries. However, It has been found that this technique does a poor job capturing detailed flow features such as the boundary layer, shoar layer, and wake of large velocity-gradient regions. Its hindrance is primarily due to the limitations of current computational resources, thus new techniques are investigated to Improve the qnallty of CFD solutions while not impeding on resources. High quality hybrid near-body volume meshes that combine atructured and unstructured meshing have been utilized to meet tha goals of the project. The area around the engine and clrculatlon control slots serves as the hasis for Improved meshing techniques. So far, a hybrid mesh has been successfully generated around the engine and the results of the CFD solutions have Improved immensely. The focus of this paper is to show a comparison of the quality of the CFD solution of old and new meshing techniques. In addition, preilminary results of a hybrid mesh around the circulation control slots are discussed and will be the focus of future work. It has been determined that the primary meshing software used, ICEM CFD does not allow enough user control to adaquate1y refIoe particular reglons In the flow field, thus, alternative meshing software will have to be explored. Current computing resources limit the total size of the mesh to about 3lI million. However, given this constraint, the results clearly show that the hybrid mesh attains more refIoed and atable CFD solutions.

Improved Meshing Technique for the Engine Exhaust of an Over-the-Wing Engine and Circulation Control Wing Configuration