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An Investigation of Air-Augmented Rocket Mixing and Combustion Process

Report Number: AFOSR 69-2951TR p. 86-91
Author: Sargent, W. H.
Author: Woodcock, K. E.
Author: Duvvuri, Tirumalesa
Author: Anderson, Ralph
Author: Channapraganda, R. S.
Corporate Author: Atlantic Research Corporation
Date of Publication: 1969-12

Abstract:
Part I

Air-augmented rocket propulsion technology was developed in a two-part program of research sponsored by the Air Force Rocket Propulsion Laboratory, Edwards Air Force Base, California, under Contract No. F04611-67-C-0011. An experimental program carried out by Atlantic Research Corporation has resulted in the development of apparatus and results which begin to define some of the dominant variable of bounded coaxial mixing and heterogeneous combustion. In particular, the effects of secondary air mass flow, chemical reactivity, particle concentration, and stream temperature are presented. The analytical program carried out by CETEC Corporation has resulted in the formulation of a theoretical model of the mixing process which includes the effects of solid particles. In addition, analysis of single particle combustion was undertaken, and good agreement between theory and existing data was achieved.

Part II

The results of past analytical studies on the fundamental aspects of two-phase turbulent mixing and solid particle ignition conducted at CETEC Corporation were applied to air-augmented ducted rockets. The present analysis includes the effects of solid phase reactions. Pressure distributions of the duct wall and mixing lengths were calculated for some specific experimental conditions for inert solid phase. The predicted axial distribution compare favorably with experimental data generated at Atlantic Research Corporation. The paper further delineates the effects of primary and secondary stream properties (i.e., stagnation temperature ratio, solids loading, Crocco number, etc.) on the mixing lengths.

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