Verification and Validation of Structured and Overset Grid Capabilities on Hypersonic Multibody Configurations

Three unit problems in shock-shock/shock-boundary layer interactions are considered in the evaluation, verification and validation of two computational codes — DPLR and US3D. The unit problems considered are those of two stacked hemispherical cylinders (of dierent diameters and lengths, and at various orientations relative to each other or relative to the nozzle axis) tested in a hypersonic wind tunnel. These problems are taken as representative of a Two-Stage-To-Orbit design. Using the same, or minimally dierent, numerical algorithms and physical models in the two computational codes, flow field solutions are calculated using dierent grid generation approaches and grid topologies — structured with point-matched grids or overset grids, and unstructured with point-matched grids. The focus of the paper is on the overset grid approach, and lessons learned in exercising this new capability in DPLR are discussed. For all approaches and grid topologies, comparisons are made against experimentally measured heat fluxes.