Abstract
A special piece of hardware (called a distortion generator) was designed using computational tools to mimic the effects of inlet distortion in a direct-connect test environment. Direct-connect simulations of scramjet combustors typically use facility nozzles designed to produce uniform flow entering the test article. However, in free-jet and flight experiments, where air is ducted to the supersonic combustor through an inlet, flow entering the test article will be inherently distorted. These distortion effects can include non- uniform boundary layer thicknesses on the walls and relatively strong oblique shock waves. In this work, the design methodology for the distortion generator is described along with details of its fabrication and installation into the experimental research facility. Finally, the results of computational and experimental calibrations are presented. Results confirm that distortion characteristics anticipated in freejet and flight experiments can be effectively simulated in the direct-connect test environment. This new hardware will enable future experimental investigations aimed at understanding the effects of inlet-induced distortion on combustor operability and performance.
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