Accession Number : AD0833236

Title :   A BOUNDARY LAYER STUDY ON HYPERSONIC NOZZLES.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s) : Shall, Paul Joseph, Jr

Report Date : MAR 1968

Pagination or Media Count : 78

Abstract : An experimental investigation was made to determine the structure and integrated properties of turbulent boundary layers in hypersonic nozzles, at Mach numbers between 10 and 12. It is concluded that the 1/7-power velocity profile does not agree with the experimental data in this Mach number range. However, a velocity profile based on the Crocco energy relations agrees well with the data as does the corresponding temperature profile, except at the point of maximum temperature. The semi-empirical relationships for boundary layer thickness and displacement thickness, proposed by Burke are strongly supported by the experimental data of this study. (Author)

Descriptors :   *TURBULENT BOUNDARY LAYER, HYPERSONIC NOZZLES, NOZZLE GAS FLOW, VELOCITY, CORRELATION TECHNIQUES, ENERGY, TEMPERATURE, THICKNESS, WIND TUNNEL MODELS, REYNOLDS NUMBER, ENTHALPY, LAMINAR FLOW, INSTRUMENTATION, TEST METHODS, STRUCTURAL PROPERTIES, COMPRESSIBLE FLOW, THESES.

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE