Abstract
The effects of injection location of secondary jet and nozzle divergent cone angle on the performance of secondary gas injection for thrust vector control (SITVC) were numerically investigated. Three-dimensional Reynolds-averaged Navier-Stokes equations with an algebraic turbulence model solved the complex three-dimensional nozzle flows perturbed by the secondary gas jet. The numerical code was properly validated by experiment. The results showed that downstream secondary jet injection and smaller nozzle divergent cone angles lead to higher efficiencies over a wide range of pressure ratios. The occurrence of reflected shock waves severely lowers SITVC propulsion performance. Upstream jet injection is more effective in a narrow range of deflection.
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