Hypersonic ramjets employing supersonic combustion of hydrogen fuel have attractive potentialities for future aircraft or launching systems. The object of the present work §§This work was sponsored by the Office of Aeronautical Research, Office of Advanced Research and Technology, National Aeronautics and Space Administration, Washington, D.C. The Applied Physics Laboratory operates under Contract NOw 62-064c with the Bureau of Naval Weapons, Department of the Navy. was to study quantitatively the effects of fuel injection parameters on the mixing of gaseous hydrogen fuel with a supersonic air stream confined within a cylindrical duct, to provide some of the fundamental background needed for the design of supersonic combustors for high-performance engines. Hydrogen was injected at sonic velocities into Mach 2 and Mach 3 air streams, at overall equivalence ratios of 0.17 to 0.50, in both radial and axial (downstream) directions from circumferential wall slots. Results showed that considerably better mixing occurred in the case of radial injection, although the decrease in stagnation pressure also was greater for this case.The eddy diffusivity of mass, Ed (turbulent diffusion coefficient) and radial velocity, Vr, were determined by differentiating experimental concentration, velocity and density profiles, obtained at various axial distances from the injection station. For the radial injection case, with a 1-in i.d. test section, a simple model in which Ed varied only in the radial direction and Vr varied only in the axial direction, allowed reasonable correlation of the experimental results. The validity of the trends obtained in Ed and Vr were checked by numerical integration of the diffusion equation, and simultaneous solution of the diffusion and momentum equations; computed profiles agreed reasonably well with downstream experimental concentration and velocity profiles. A method for solving turbulent mixing problems by simultaneous solution of the diffusion, momentum and energy equations is presented.
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