Abstract
An optimization analysis is presented for the design of maximum thrust nozzles which contain liquid or solid particles in the flowfield. A design procedure was developed wherein an assumed nozzle contour is analyzed to determine if it is a maximum thrust nozzle, and a relaxation scheme was employed to modify the assumed contour until the maximum thrust contour is obtained. Parametric studies were conducted to illustrate the influence of the particle size, the nozzle inlet angle, the throat radius of curvature, the particle drag and heat-transfer coefficients, the particle to gas mass flow ratio, and the nozzle size.
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Schedule a callMore From: AIAA journal. American Institute of Aeronautics and Astronautics
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