This report describes the work performed under Contract AF 04(611)-9073 during the second, quarter of the contract period, beginning September 1963. The objectives of the study are:n(a) To develop design tools, in the form of digital computer programs for the nozzle designers to use for calculating the behavior of materials exposed to a solid-propellant rocket-exhaust environment.n(b) To marshal 1 existing theoretical methods, and to extend these or develop new methods where necessary, to gain a better understanding of the fundamental mechanisms associated with exposed materials behavior in a rocket nozzle environment.nThe work during this quarter has been directed toward the development of a digital computer program applicable to materials such as tungsten and graphite,- that, in general, do not erode appreciably or that erode with one moving boundary. This has required effort in the areas of convective heat transfer, transient conduction, equilibrium chemistry, reaction kinetics, and mass transport, as applied to the solid-propellant rocket problem, and this work is discussed in detail. Further, a plasma-generator rocket simulation-test program has been formulated to complement the theoretical studies, and the test program and some firing results are described.
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