1. Algorithm Artificial compressibility Symmetric Coupled Gauss Seidel Parallel Pressure (SCGS-PP) 1st, 3rd and 5th order convective schemes 2nd, 4rd and 6th order representations for the diffusive, pressure gradient and divergence terms Collocated and staggered grids Nth order fully implicit time integration Explicit time integration possible (convection & diffusion) Multigrid (collocated grid code) Parallelized using Message Passing Interface (MPI) and domain decomposition. Immersed boundary method for complicated geometry's

2. Results Normal injection, blowing ratio of.5 2.14 million grid points with heat transfer, Re 2000 3.5 million grid points with a plenum, Re 4700 5.2 million grid points with heat transfer, Re 2000 No perturbations in flow field

3. Compressible N-S equations The artificial compressibility method for the incompressible N-S equations is essentially equivalent to low Mach number preconditioning for the compressible N- S equations. Since we are interested in subsonic flows the differencing schemes should not have to change. The current capability of N scalars will be replaced with N ideal gases. This will ease the addition of reactions in possible future work.

4. Top view

5. Side view

6. Budgets Term by term analysis of RANS models Determine validity of various turbulence model assumptions for this class of flows. Bottom Line: Improvements in turbulence models for film cooling.

7. GOALS Use DNS data to improve RANS models for film cooling. DNS provides a wealth of information on all aspects of a flow Use this information to do term by term analysis of RANS models Determine validity of various turbulence model assumptions for this class of flows. Bottom Line: Improvements in turbulence models for film cooling.

8. 2.14 million grid points

9. 3.5 million grid points with plenum