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Algorithm

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

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Algorithm

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  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. 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.

  3. 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

  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

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