Effects of Cone Tip Changes On Wall-Cooled Hypersonic Boundary Layer Transition and Turbulence
Date of Award
Master of Science
Department of Aeronautics and Astronautics
Mark F. Reeder, PhD
Boundary layer measurements took place at Air Force Research Lab’s (AFRL) Mach-6 Ludwieg tube hypersonic wind tunnel on a 7-degree half angle spherically blunted nose cone with a 1.5 mm radius to study the effects of a cooled surface on the transition process. Experiments compared uncooled and cooled flow conditions on the blunt-nosed model, and then compared to past data for a sharp-tipped cone of similar geometry. Cooling the surface delayed the onset of transition on the blunt nose model. Combining the effects of nose blunting and cooling further increased transition delay than each acting individually compared to the sharp-tipped case. This outcome provides much needed data in an area of study with inconclusive results.
DTIC Accession Number
Major, Mathew M., "Effects of Cone Tip Changes On Wall-Cooled Hypersonic Boundary Layer Transition and Turbulence" (2022). Theses and Dissertations. 5441.