Input of the supersonic air and hypersonic two-dimensional and symmetrical to the combustion air of a motor 371

摘要

Air inlet for the two-dimensional supersonic and hypersonic combustion air of an aircraft engine, comprising two front flaps 3 forming a visor disposed symmetrically on either side of a longitudinal plane p, characterized by the fact that each front flap 3 is movable about a pivot axis 4 situated in the vicinity of the wall of the air intake which extends the front flap considered.