Patent ID: 7533517

Claim:
An exhaust nozzle for an engine of a flying craft, comprising: a tubular body with two outlet ducts defining, in the upstream direction, a primary gas flow path divided, in the downstream direction, into two parallel secondary gas flow paths, wherein each of the two outlet ducts comprises a box for injecting gas into a corresponding secondary path, each box being attached to a lateral wall of a corresponding outlet duct in an intermediate space formed between downstream sections of the outlet ducts and each box having a window aligned with a slot formed in the lateral wall of the corresponding outlet duct, and an adjustment mechanism configured to adjust a direction of an outflow of gas injected through said window into the secondary path, wherein said adjustment mechanism is configured to adjust the direction of said outflow of gas between a direction perpendicular to said secondary path and a non-perpendicular direction oblique relative to said secondary path.