An aerodynamic model is proposed for the exhaust plume issuing from a rocket nozzle exit into quiescent ambient air in which chemical reaction or two-phase flow does not predominate. The model is based on the presently available knowledge and established aerodynamic principles for the various flow regimes involved. The major assumptions made are individually substantiated and justified by experimental evidence in existing literature. A theoretical analysis is carried over the whole flow region based on the Karman's integral approach in the hope of finding solutions for the gross aerodynamic behavior of the plume, especially for ranges up to the full region of the plume. Solutions are matched at the boundary of the inviscid core and turbulent mixing regions. Theoretical results agree closely with related experimental data. (Author)


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