Visualization of the structure of supersonic turbulent boundary layers

摘要: A series of flow visualizations has been performed on two flat-plate zero-pressure-gradient supersonic boundary layers. The different layers had moderate Mach numbers 2.8 and 2.5 Reθ's 82, 000 25, respectively. number new visualization techniques were applied. One was a variation conventional schlieren employing “selective cut-off” at the knife edge plane. Motion pictures generated with this technique. Droplet seeding also used to mark flow, high speed movies made show structure evolution. Still taken details within large-scale motions. Finally, Rayleigh scattering construct planar images flow. Together, these provide detailed information regarding character kinematics motions appearing in Using data, concert existing hot-wire some suggestions are characteristics “average” motion.