Fluid-dynamic shock ring for controlled flow separation in a rocket engine exhaust nozzle

摘要

A rocket engine designed for high altitude operation with a large area ratio nozzle, is operated efficiently at sea level through controlled flow separation of the primary gas stream by generating a fluid-dynamic "shock ring" at a specified area ratio forcing the primary gas stream boundary layer to separate uniformly from the nozzle wall. The fluid-dynamic shock ring is generated by injecting uniformly a gas or liquid of low mass through a multitude of small holes or a circumferential slot extending the full circumference of the nozzle wall.