Development of a Flow Field for Testing a Boundary-Layer-Ingesting Propulsor

Abstract: In order to test embedded-propulsor technology, modifications were required of the 8×6 Supersonic Wind tunnel at NASA Glenn Research Center. The extent of the modifications required that a new tunnel calibration be completed to generate a new calibration dataset and operational procedures for the tunnel, as well as to map the boundary layer on the raised floor. This report describes the propulsor inflow that was to be simulated, documents the tunnel modifications that were required, and conve…

Source:: nasa sti