Improved Simulation of Inflow Distortion for Direct- Connect Scramjet Studies

摘要

A technique to develop flight-like inflow conditions for direct-connect testing has been extended in the current work. This technique utilizes an expansion/contraction section upstream of the engine isolator in a direct-connect test facility to create shock waves consistent with those generated in flight. The current work improves upon the earlier work by better matching the inlet shock structures, the average conditions at the engine throat, and boundary layer properties. RANS CFD simulations have been performed for isolators downstream of a flight inlet, a direct-connect facility nozzle without distortion, and a direct-connect facility nozzle with distortion. The RANS CFD simulations predict similar shock positions in all cases, however a change in the mass flux distribution at the exit plane is observed.