Combustion Dynamics in Rockets.
Annual rept. 1 Oct 83-30 Sep 84,
GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING
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Progress is reported on two distinct projects which are administered as a group. A summary for each task follows Task I Laser velocimetry has mapped two velocity component data for the backward facing step facility with and without blowing of air and CO2 from the bottom wall of the facility. Comparison of experiment with theory, using a k-epsilon tubulence model, has shown good agreement between the two. Diagnostic development has continued with the Rayleigh scattering system how operational and the Raman spectroscopy system still under development. Software development for simultaneous Rayleigh concentration and laser velocimeter measurements has been completed. Dominant results are the general predictability of the length scales of the flow field and the appearance of a second recirculation zone under the action of sidewall blowing. Studies continued on the behavior of aluminum and other nonvolatile ingredients in the propellant combustion zone. A method for observation of particle behavior and interaction during controlled heat-up was developed using an improvised hot stage in the scanning electron microscope. Notable difference was observed in this experiment in behavior of aluminum from different sources.
- Combustion and Ignition
- Solid Rocket Propellants