A diverterless hypersonic inlet (DHI) for a high speed, air-breathing
propulsion system reduces the ingested boundary layer flow, drag, and
weight, and maintains a high capture area for hypersonic applications.
The design enables high vehicle fineness ratios, low-observable features,
and enhances ramjet operability limits. The DHI is optimized for a
particular design flight Mach number. A forebody segment generates and
focuses a system of multiple upstream shock waves at desired strengths
and angles to facilitate required inlet and engine airflow conditions.
The forebody contour diverts boundary layer flow to the inlet sides,
effectively reducing the thickness of the boundary layer that is ingested
by the inlet, while maintaining the capture area required by the
hypersonic propulsion system. The cowl assembly is shaped to integrate
with the forebody shock system and the thinned boundary layer region.