Accession Number : ADA307271
Title : Turbulence, Heat-Transfer, and Boundary Layer Measurements in a Conical Nozzle with a Controlled Inlet Velocity Profile.
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER
Personal Author(s) : Boldman, Donald R. ; Schmidt, James F. ; Fortini, Anthony
PDF Url : ADA307271
Report Date : MAR 1966
Pagination or Media Count : 29
Abstract : Turbulence, heat-transfer, and boundary layer measurements were obtained in a conical nozzle operating in air at a nominal total temperature and pressure of 960 deg. R and 300 psia, respectively. Experimental heat-transfer coefficients were compared to values determined by three prediction techniques; namely, (1) Nusselt number correlation, (2) a compressible boundary layer theory, and (3) an incompressible boundary layer theory. Methods (1) and (2) yielded nozzle heat-transfer coefficients that were appreciably higher than experimental values; however, method (3) predicted the nozzle heat-transfer coefficients very well yielding results that were within about 2 percent of the experimental values at the throat. In part of the investigation a simulated nuclear reactor core turbulence generator installed 3 inches upstream of the cylindrical inlet failed to alter the nozzle heat-transfer coefficients. In addition, the turbulence generator had essentially no effect on the boundary layer temperature profiles in the nozzle.
Descriptors : *BOUNDARY LAYER, *TURBULENCE, *HEAT TRANSFER COEFFICIENTS, VELOCITY, PRESSURE GRADIENTS, AIR FLOW, TURBULENT FLOW, HEAT EXCHANGERS, CORRELATION, COMPRESSIBLE FLOW, TEMPERATURE GRADIENTS, MATHEMATICAL PREDICTION, THERMAL CONDUCTIVITY, MACH NUMBER, HEAT FLUX, SURFACE TEMPERATURE, INLETS, STATIC PRESSURE, PRESSURE DISTRIBUTION, REYNOLDS NUMBER, INCOMPRESSIBLE FLOW, NOZZLE THROATS, STAGNATION TEMPERATURE, NOZZLE GAS FLOW, STAGNATION PRESSURE, ROCKET NOZZLES, CONICAL NOZZLES.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE