Active magnetic control thermal protection device of hypersonic aircraft and flow field parameter calculation method

The invention belongs to the field of fluid mechanics flow control and the field of plasma physical application, and discloses an active magnetic control thermal protection device of a hypersonic aircraft and a flow field parameter calculation method. The device comprises an insulating layer, an electrified solenoid magnet and an alkali metal-impregnated pyrolysis material layer, the insulating layer is located on the blunt front edge of the aircraft shell, the surface is covered with the alkali metal-impregnated pyrolysis material layer, and the electrified solenoid magnet is fixed in a cavity of the aircraft shell. The active magnetic control thermal protection device performs magnetic field interference on plasmas existing at a blunt end or a blunt front edge or artificially formed, so that the heat flux of the wall surface of the hypersonic aircraft is reduced, the heat flux is further reduced, and thermal protection is realized. The flow field parameter calculation method comprises the following steps: e