Abstract
Theme A analysis using the method of characteristics with heat addition and the Crocco-Lees base flow model is described for calculating the external supersonic flow with heat addition about the wake of a 5-in. projectile. Various amounts and locations of heat addition are found to generate a net thrust, and an optimum location for the combustion zone is predicted. Good agreement is observed between calculated and experimental base pressure measurements using a free-jet combustion simulator. The results from computing base pressure ratio over a wide range of Reynolds numbers are also presented.
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