Abstract: NASA has successfully developed a new testbed configuration for experimentally evaluating embedded boundary layer ingesting aircraft propulsors in its 8’x6′ Supersonic Wind Tunnel. This testbed meets the challenges of providing the necessary freestream flow Mach conditions and desired range and distribution of boundary layer thickness for embedded aircraft propulsion systems. The testbed consists of a 48ft long raised wind tunnel floor aircraft surface simulator and a boundary layer regulatio…