Example of MacroCell Domain Decomposition for Two-Dimensional Flow Over a Circular Cylinder.

	Computed Instantenous Vorticity Field in the Leading Edge Region of a NACA-0012 airfoil at 15 degrees angle of attack and a chord Reynolds number of 400,000. This Snapshot Corresponds to a Non-Dimensional Time tU/c of 0.09 After Vorticity is Impulsively Released From the Airfoil Surface (see References for further detail).
	Contours of Local Spectral Error (Corresponding to Flowfield in Figure Above) Indicating the Need for Streamwise Grid Refinement in Feeding Vorticity Sheet and Secondary Shear Layer Regions. Further details about this method can be found in [AIAA Paper 99-0300].