This invention relates to the field of supersonic inlet start-up and active flow control technology, aiming to solve the problems of
inlet flow separation,
shock wave boundary layer interference, and start-up
lag in existing
scramjet engines. It provides a miniature
supersonic nozzle array device and engine for enhancing inlet start-up. The miniature
supersonic nozzle array device includes a rotating mechanism on which multiple nozzles are mounted, arranged at intervals. The
airflow channel inside each
nozzle is an acceleration channel, and the
airflow channel between two adjacent nozzles is a deceleration channel. The acceleration channel is sequentially divided into an acceleration
channel inlet section, a central contraction section, and an acceleration channel outlet section along the gas flow direction. The cross-sectional size of the central contraction section is smaller than that of the acceleration
channel inlet section and the acceleration channel outlet section. This invention effectively solves the problems of
shock wave boundary layer interference, flow separation, and start-up
lag at the inlet lip under high Mach number conditions.