No abstract

No abstract

No abstract

No abstract

The test section of the 8-by 6-Foot Supersonic Wind Tunnel at NASA Glenn Research Center was modified to produce the test conditions for a boundary-layer-ingesting propulsor. A test was conducted to measure the flow properties in the modified test section before the propulsor was installed. Measured boundary layer and freestream conditions were compared to results from computational fluid dynamics simulations of the external surface for the reference vehicle. Testing showed that the desired freestream conditions and boundary layer thickness could be achieved; however, some non-uniformity of the freestream conditions, particularly the total temperature, were observed. Nomenclature 86 SWT 8-by 6-Foot Supersonic Wind Tunnel BL Boundary Layer BLI Boundary Layer Ingesting BWB Blended Wing Body CFD Computational Fluid Dynamics TS Tunnel Station, in. h height of the boundary layer thickening pins, in. u velocity in the streamwise direction, ft/s U ∞ freestream velocity in the streamwise direction, ft/s x axial coordinate, tunnel station, in. y transverse coordinate, in. z vertical coordinate, in.  boundary layer thickness (99 percent of the freestream velocity), in.