Maximum Thrust Nozzles for Nonequilibrium Simple Dissociating Gas Flows

Abstract

A formulation, numerical solution technique, and computer program implementing the technique are presented for the design of maximum thrust nozzles for rotational or nonequilibrium simple dissociating gas flows including boundary-layer effects. The formulation is based on the usual assumptions applicable to rotational and nonequilibrium simple dissociating gas flows and on the assumption that the boundary layer is thin. The thrust is maximized by application of the calculus of variations. The resulting design equations are hyperbolic partial differential equations, which are solved by the method of characteristics. The results of a study to determine the magnitude of the performance increases that can be expected by considering more accurate flow chemistry models are presented. The results indicate that significant performance improvements may be possible.