Akademik Veri Yönetim Sistemi
AIAA Journal, cilt.33, sa.5, ss.805-811, 1995 (Scopus)
The experimental documentation of a three-dimensional shock-wave/boundary-layer interaction in a nominal Mach 3 flow is presented. The model consisted of a sting-supported cylinder, aligned with the freestream flow, and a 20-deg half-angle conical flare offset 1.27 cm from the cylinder centerline. Surface oil flow, laser light sheet illumination, and spark schlieren photography were used to document the flow topology. Extensive surface-pressure and skin-friction measurements were made throughout the interaction region. A laser interferometric skin-friction instrument was employed to acquire the skin-friction data. Resolved skin-friction measurements of CfxE and Cfz were made within the highly swept three-dimensional separated regions. The skin-friction data will be of particular value for turbulence modeling and computational fluid dynamics validation. © 1995, American Institute of Aeronautics and Astronautics, Inc., All rights reserved.