Accession Number : AD0759563

Title :   Methods for Distinguishing Type of Hypersonic Boundary Layer in Shock Tunnel.

Descriptive Note : Research rept.,

Corporate Author : GENERAL ELECTRIC CO SCHENECTADY N Y RESEARCH AND DEVELOPMENT CENTER

Personal Author(s) : Sheer,R. E. , Jr. ; Nagamatsu,H. T.

Report Date : DEC 1967

Pagination or Media Count : 15

Abstract : An experimental program for studying the transition phenomenon, boundary layer characteristics, and local heat transfer rates on 4- and 8-foot long 10 deg included angle cones in a hypersonic chock tunnel has brought about the development and improvement of instrumentation and methods for distinguishing hypersonic laminar, transition, and turbulent boundary layers in relatively short test time experimental facilities. The methods used include schlieren optics, local heat transfer rates from thin-film sputtered platinum surface gauges, and surveys through the boundary layer using impact pressure, total temperature, and thin heat transfer wedges. Also, the actual oscilloscope traces, directly from the heat transfer instrumentation, be used to define the type of boundary layer. (Author)

Descriptors :   (*REENTRY VEHICLES, BOUNDARY LAYER TRANSITION), HYPERSONIC CHARACTERISTICS, HEAT TRANSFER, SHOCK TUBES, FLOW FIELDS, INSTRUMENTATION, OSCILLOSCOPES, LAMINAR BOUNDARY LAYER, TURBULENT BOUNDARY LAYER, PROBES, CONICAL BODIES, SURFACE PROPERTIES

Subject Categories : Guided Missile Reentry Vehicles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE