The Effect of an Intense Magnetic Field on Rocket Nozzle Heat Transfer. Part 1: Theory and Superconducting Magnet Experiments

摘要

A theoretical and experimental investigation of the effect of an axial magnetic field on rocket nozzle heat transfer is reported. Results of heat transfer experiments using an aircore superconducting solenoid were inconclusive. For magnetic flux densities up to 1.5 webers/sq m there was no observable change in heat transfer from the combustion gas to the rocket nozzle wall. Rocket engine vibration decreased the stability of superconducting solenoid operation; in turn, the magnetic field perturbed the ignition characteristics and combustion chamber pressure of the rocket engine. The experimental investigation is continuing and will use a cryogenically-cooled magnet powered by a battery bank; results from this investigation will be documented in Part II of this Report. (Author)