Design of Maximum Thrust Nozzles with Nonequilibrium, Chemically Reacting Flow. Volume I. Theoretical Development and Results.
Final technical rept. 1 Jan 69-31 Aug 71,
PURDUE UNIV LAFAYETTE IND JET PROPULSION CENTER
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An analysis is presented which permits the design of maximum thrust nozzles for nonequilibrium chemically reacting gas flows. The analysis is based upon the governing equations for a general, multi-component reacting gas. The effects of viscosity, multiple phases, body forces and mixing are neglected. All other states of the gas are assumed to be in equilibrium. Design of the nozzle contour is posed subject to a general isoperimetric constraint. The thrust to be maximized is written in terms of an integral of the pressure forces on the nozzle wall. The design constraints and governing equations are incorporated into the integral to be maximized by means of Lagrange multipliers. Author
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