Accession Number : AD0484667

Title :   MEASUREMENT OF RADIANT HEAT TRANSFER TO THE FUEL GRAIN SURFACE IN A HYBRID ROCKET USING THIN FILM RESISTANCE THERMOMETERS.

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : Searle, Henry L.

Report Date : MAY 1966

Pagination or Media Count : 94

Abstract : Measurement of the heat transfer to the pyrolyzing solid fuel surface is a necessary step in the continuation of analysis of hybrid rocket combustion phenomena. Thin film resistance thermometers were used to measure the radiative component of energy transfer from the flame zone to the fuel surface. A slab grain combustion chamber, which provided a planar flame zone in a flat plate boundary layer, was designed and utilized in this investigation. The existing hybrid rocket test apparatus was also used after extensive redesign of the supply, control, and instrumentation systems. Fuels studied were polystyrene and aluminum filled plexiglas with oxygen used as oxidizer. Radiant heat flux values were obtained in the slab burner at chamber pressures from nine to fifteen atmospheres with oxidizer flow rates above 0.15 lbm/sq in-sec. Radiant energy transfer to the fuel surface appears to increase with pressure and decrease with oxidizer flux as expected. (Author)

Descriptors :   *HEAT TRANSFER), (*HYBRID ROCKET ENGINES, MEASUREMENT, RESISTANCE THERMOMETERS, SOLID ROCKET FUELS, COMBUSTION, CAPTIVE TESTS, STYRENE PLASTICS, ACRYLIC RESINS, IMPREGNATION, ALUMINUM, OXIDIZERS, LIQUEFIED GASES, OXYGEN, ROCKET PROPELLANT GRAINS.

Subject Categories : Rockets

Distribution Statement : APPROVED FOR PUBLIC RELEASE