Accession Number : AD0780691

Title :   Interacting Supersonic Turbulent Boundary Layers Over a Two-Dimensional Protuberance.

Descriptive Note : Technical rept.,

Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s) : Polak,Arnold

Report Date : 21 JAN 1974

Pagination or Media Count : 25

Abstract : The report presents a numerical study of attached interacting supersonic turbulent boundary layers over a two-dimensional protuberance. Results are presented in terms of surface pressure, heat transfer and skin-friction distributions. These results indicate a strong effect of the size of the protuberance, Mach number, but a weak effect of Reynolds number and the ratio of wall-to-recovery temperature. The peak heating rates from a set of test cases compare well to a semi-empirical prediction method. In contradistinction to the laminar case, the turbulent recovery zone downstream of the protuberance is very short. (Author)

Descriptors :   *Aircraft protuberances, *Supersonic characteristics, Surface properties, Turbulent boundary layer, Two dimensional flow, Interactions, Pressure, Aerodynamic heating, Flow fields

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE