An Ejector Air Intake Design Method for a Novel RBCC Rocket Nozzle

An air intake design methodology for a novel rocket nozzle geometry is presented. The novel rocket nozzle is intended for use in rocket based combined cycle vehicles (RBCC) and thus incorporates openings for air intakes. The intake geometry, which consists of a center body, a cowl, and fairings, is designed to minimize total pressure losses while maximizing mass ∞ow rate through the nozzle openings. Six geometric design parameters are required to fully deflne the intake geometry. A ∞ow analysis, which combines an axisymmetric inviscid panel method and an integral boundary layer method, is used to predict the air intake performance based on mass ∞ow rate. Initial comparisons between the ∞ow analysis and 3D numerical simulations show mass ∞ow rate predictions within 4.72% of the 3D numerical simulations.