Abstract
This paper examines the three-dimensional shock-wave/turbulent boundary-layer interaction in an inletlike geometry consisting of symmetrically placed 15-deg fins on a plate in an oncoming Mach 4 flow. Two different implicit numerical methods are employed to solve the full three-dimensional mean compressible Navier-Stokes equations: 1) a high resolution upwind scheme with the Baldwin-Lomax algebraic turbulence model and 2) the traditional Beam-Warming approach with a k-e model. The comparison with experiment is very good for surface pressures, pitot pressure surveys, and surface shear patterns, although discrepancies with skin friction data are evident in the trailing portion of the interaction. Both computational schemes, despite major differences in modeling, predict similar flow structures in agreement with previous results at Mach 8. The flow is described in terms of a separated, nonreattaching boundary layer, a vortex interaction, longitudinal centerline vortices, and entrainment. The computed and experimental shock patterns are related to the streamline structure to provide a unified understanding of the flowfield.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
