Project 8: Development and Validation of Bleed Models for Control of Supersonic Shock-Wave Interactions with Boundary Layers

Numerical Analysis Numerical simulations will be conducted on a supersonic engine inlet with a specified geometry. The solution to the compressible Navier-Stokes equations will resolve the flow field inside the bleed passages within a domain that spans between the multiple bleed rows.

Grid Generation and Setup Particular attention in the analysis will be paid to the domains above the plate, within the bleed holes and plenum. The grids will be clustered near the bleed plate surface and within the bleed holes.

Validation of Model A range of external Mach and Reynolds numbers, and shock strengths will be explored in order to validate the developed bleed model adaptation to shock interactions with porous bleed in full scale applications and wind tunnel tests.