Abstract
The damping of axial instabilities by a variety of small-scale solid rocket nozzles has been determined experimentally under cold-flow conditions using the modified impedance tube technique. The dependence of the damping upon the cavity depth and the secondary flow rate issuing from the cavity of a submerged nozzle, the geometry of the convergent section of a single-ported nozzle, and the number of nozzles present in a multipleported nozzle cluster has been determined. Measured data indicate that in the case of the submerged nozzle the cavity depth surrounding the nozzle has a significant effect upon the nozzle admittance while the secondary flow rate issuing from the cavity has negligible effect on the admittance. Tests conducted with conical, equal-radii-ofcurvature and linear-velocity-profile nozzles showed that conical nozzles provide the most damping. Tests with multiple-ported nozzles indicated that quadruple-ported nozzles provide less damping for axial instabilities than single and dual-ported nozzles whose damping capabilities are approximately the same.
Published Version
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