Abstract
To confirm the possibility of the controllability of the highly heated gas associated with a reentry flight, or the reduction of the heat load to a reentry vehicle, we experimentally examine the electro-magnetic shield effect on a weakly ionized argon plasma supersonic flow around a body, around which the magnetic field is generated. To analyze the flow, the flow visualization and the spectroscopic measurement of the self-radiating flow were carried out. Based on the spectroscopic measurements, the electron excitation temperature was determined by means of the line intensity method. The possible shock front in front of the body was identified from the electron excitation temperature distribution. It was found that, as theoretically suggested, the possible shock stand-off distance is influenced by the application of the magnetic field and becomes larger than the one without the magnetic field.
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