INVESTIGATION OF A CONTOURED WALL INJECTOR FOR HYPERVELOCITY MIXING AUGMENTATION

An experimental and computational investigation of a contoured wall fu el injector is presented. The injector was aimed at enabling shock-enh anced mixing for the supersonic combustion ramjet engines currently en visioned for applications on hypersonic vehicles. Three-dimensional fl owfield surveys and temporally resolved, planar Rayleigh scattering me asurements are presented for Mach 1.7 helium injection into Mach 6 air . These experimental data are compared directly with a three-dimension al Navier-Stokes simulation to provide a detailed characterization of the now about the injector array. Time-mean mixing rate data and preli minary conclusions concerning various sources for axial vorticity are presented.