Accession Number : ADA307203

Title :   Startup of the Liquid-Metal Heat Pipe in Aerodynamic Heating Environments.

Descriptive Note : Final rept. 1 Jul 95-31 Jan 96,

Corporate Author : WRIGHT LAB WRIGHT-PATTERSON AFB OH

Personal Author(s) : Chang, Won S.

PDF Url : ADA307203

Report Date : FEB 1996

Pagination or Media Count : 51

Abstract : As part of a US Army missile development program, liquid-metal heat pipes have been investigated to remove the high heat flux associated with the missile fins being located in hot exhaust gas paths. Using steady-state and transient analyses, a solution method has been developed to identify the required length of the condenser for a design operation when the heat pipe is coupled with aerodynamic heating and cooling environments. A simple transient analysis using the lumped heat-capacity method predicts the response of operating temperatures and the propagation of the continuum' front when the liquid-metal heat pipe is started from the frozen state.

Descriptors :   *AERODYNAMIC HEATING, *HEAT PIPES, STEADY STATE, TRANSIENTS, HIGH TEMPERATURE, SHOCK WAVES, AIR FLOW, COOLING, TEMPERATURE GRADIENTS, THERMAL ANALYSIS, THERMAL CONDUCTIVITY, HOT GASES, MACH NUMBER, SUPERSONIC FLOW, CONVECTION(HEAT TRANSFER), HEAT FLUX, FREE STREAM, SURFACE TEMPERATURE, VISCOSITY, SURFACE TO SURFACE MISSILES, LAMINAR FLOW, JET FLOW, GUIDED MISSILE COMPONENTS, REYNOLDS NUMBER, THERMAL STRESSES, HEAT SINKS, FINS, EVAPORATORS, HEAT TRANSFER COEFFICIENTS, CONDENSERS(LIQUEFIERS), LIQUID METALS, EXHAUST GASES.

Subject Categories : Air Condition, Heating, Lighting & Ventilating
      Guided Missile Dynam, Config & Cntrl Surfaces
      Surface-launched Guided Missiles
      Thermodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE