Abstract
A passive method of controlling normal shock/boundary layer interactions (SBLIs) for external compression inlet applications is the use of micro-ramps for boundary layer control (BLC). These devices were placed upstream of normal SBLIs of various shock strengths and analyzed with Reynolds Averaged Navier-Stokes (RANS) CFD. A simplified CFD model produced normal shock phenomena identical to that encountered near the throat of an external compression inlet. Micro-ramp configurations were compared to baseline no flow control cases, and both qualitative and quantitative performance metrics were assessed. Simulations indicated that micro-ramps have the potential to reduce BL separation and improve inlet performance as well as the potential to improve stability for normal SBLIs. Converged RANS solutions were demonstrated up to normal shock strength of Mach 1.8. A preliminary hybrid RANS / Large Eddy Simulation (LES) investigation was also performed, indicating that further research should move in the direction of time accurate CFD and experiment to assess the dynamic flow environment and stability characteristics introduced by the passive devices. Based on the results of this study further investigation of passive devices is warranted to achieve the goal of zero bleed inlets for supersonic aircraft.
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