Accession Number : AD0615734

Title :   THE EFFECT OF AN INTENSE MAGNETIC FIELD ON ROCKET NOZZLE HEAT TRANSFER. PART 2. CRYOGENIC ELECTROMAGNET EXPERIMENTS.

Descriptive Note : Rept. for Nov 63-Jul 64,

Corporate Author : NAVAL ORDNANCE TEST STATION CHINA LAKE CALIF

Personal Author(s) : Krzycke,Leroy J. ; Lee,James B.

Report Date : MAR 1965

Pagination or Media Count : 44

Abstract : The report describes a theoretical and experimental investigation of the effect of an axial magnetic field on rocket nozzle heat transfer. The expected reduction in heat transfer was predicated on the anisotropy in the transport coefficients of a partially ionized gas in a magnetic field. Calculations of the electrical properties of the nozzle core and boundary layer gases were made using advanced chemical equilibrium and boundary layer heat transfer computer programs. The gas electrical conductivity and electron density decreased by a factor of ten in the turbulent boundary layer and by an even greater factor in the laminar sub-layer. A 5. 3-T magnetic field, generated by a force-cooled cryogenic electromagnet, failed to produce a detectable change in the heat transfer from the seeded hydrocarbon combustion gases to a water-cooled copper rocket nozzle wall. This result was insensitive to field direction. The boundary layer gases were insufficiently ionized for a measurable interaction with the magnetic field. (Author)

Descriptors :   (*MAGNETIC FIELDS, ROCKET NOZZLES), (*ROCKET NOZZLES, MAGNETIC FIELDS), (*HEAT TRANSFER, ROCKET NOZZLES), ELECTROMAGNETS, CRYOGENICS, TURBULENT BOUNDARY LAYER, GASES, SOLENOIDS, ELECTRICAL CONDUCTIVITY, ELECTRON DENSITY

Distribution Statement : APPROVED FOR PUBLIC RELEASE