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.