Experimental investigation of the flow field in the head-end star slot section of a solid rocket motorA test program has been developed to investigate the complex flowfield in the head-end, star grain section of a solid rocket motor. Documentation of the flowfield pattern is to be obtained using both flow visualization techniques and quantitative methods, including static pressure measurements, heat transfer coefficient measurements, and hot-wire anemometry. A cold-flow, one-tenth-scale model based on the geometry of the Space Shuttle SRM head-end section and its single-port igniter, along with two models of a four-port igniter, have been constructed. The scale factor is derived from a scaling analysis which matches Reynolds number between the model and the full-scale flowfield in the star grain section. The NASA Marshall Space Flight Center 14 x 14 inch trisonic wind tunnel will be utilized for the cold flow tests. Since the work is still in progress, no results are included.
Document ID
19910059616
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ciucci, A. (Auburn Univ. AL, United States)
Foster, Winfred A., Jr. (Auburn Univ. AL, United States)
Jenkins, Rhonald M. (Auburn University AL, United States)