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- W2000655151 abstract "*† ‡ Numerical results are presented from a reacting-flow Navier-Stokes simulation of a rocket nozzle in which fuel is injected downstream of the nozzle throat for the purposes of augmenting the thrust. The numerical results are compared with experimental data in terms of overall thrust and specific impulse as well as pressure distribution along the nozzle wall. The flow physics associated with the thrust augmentation is also described. The investigation shows that propellant injection downstream of the throat is a viable method for augmenting rocket thrust. In addition, the augmented thrust levels increase with increasing levels of injected mass flow. Finally, the investigation shows that the numerical predictions are in good agreement with the experimental results. Nomenclature P = pressure M = Mach number TAN = thrust augmented nozzle X = axial distance along nozzle L = nozzle length subscripts ref = reference conditions T = stagnation conditions" @default.
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- W2000655151 date "2006-07-09" @default.
- W2000655151 modified "2023-09-24" @default.
- W2000655151 title "Numerical Simulation of a Thrust Augmented Rocket Nozzle" @default.
- W2000655151 doi "https://doi.org/10.2514/6.2006-5205" @default.
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