LAUSR

Vortex generators within a two-dimensional external-compression supersonic inlet for Mach 1.6 were investigated to determine their ability to increase total-pressure recovery, reduce total-pressure distortion, and improve the boundary layer. The vortex generators studied included vanes and ramps. The geometric factors of the vortex generators studied included height, length, spacing, and positions upstream and downstream of the inlet terminal shock. The flow through the inlet was simulated through the computational solution of the steady-state Reynolds-averaged Navier–Stokes equations on multiblock structured grids. The vortex generators were simulated by either gridding the geometry of the vortex generators or modeling the vortices generated by the vortex generators. The inlet performance was characterized by the inlet total-pressure recovery, total-pressure distortion, and incompressible shape factor of the boundary layer at the engine face. The results suggested that ramps were not effective, and only ...