Accession Number : ADA289393
Title : Investigation of Boundary Layer and Performance Effects of Transpiration Cooling Through a Porous Plate in a Rocket Nozzle.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Keener, David N.
PDF Url : ADA289393
Report Date : DEC 1994
Pagination or Media Count : 116
Abstract : This study used a range of low blowing ratios with air through an area of porous material in a Mach 2.0 nozzle to quantity the change in boundary layer thickness as a function of blowing ratio. Also, exit and wall Mach number profiles at each blowing ratio were collected to characterize performance losses as a result of blowing. Performance in terms of specific impulse was also studied. As expected, the boundary layer thickness increased and nozzle performance in terms of exit Mach number decreased with increasing blowing ratio.
Descriptors : *FILM COOLING, *POROUS MATERIALS, *ROCKET NOZZLES, PRESSURE GRADIENTS, RATIOS, PERFORMANCE(ENGINEERING), TRANSPIRATION, WALLS, MACH NUMBER, SPECIFIC IMPULSE, BOUNDARY LAYER FLOW, HEAT LOSS.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE