AN EXPERIMENTAL STUDY OF BOUNDARY LAYER PARAMETERS AT THE EXIT OF A HYPERSONIC CONTOURED NOZZLE.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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The boundary layer thickness and displacement thickness were experimentally evaluated at the exit plane of an arc heated 9.492 inch exit diameter hypervelocity M or 8 contoured nozzle for both equilibrium and nonequilibrium flows. It was concluded that the boundary layers were turbulent and the use of a plenum chamber decreases the displacement thickness for identical arc heater stagnation chamber conditions. Author