A sub-scale experimental static investigation of anaxisymmetric nozzle with fluidic injection for thrust vectoringwas conducted at the NASA Langley Jet Exit Test Facility.Fluidic injection was introduced through flush-mountedinjection ports in the divergent section. Geometric variablesincluded injection-port geometry and location. Test conditionsincluded a range of nozzle pressure ratios from 2 to 10 and arange of injection total pressure ratio from no-flow to 1.5.The results indicate that fluidic injection in anaxisymmetric nozzle operating at design conditions producedsignificant thrust-vector angles with less reduction in thrustefficiency than that of a fluidically-vectored rectangular jet. Theaxisymmetric geometry promoted a pressure relief mechanismaround the injection slot, thereby reducing the strength of theoblique shock and the losses associated with it. Injection portgeometry had minimal effect on thrust vectoring.
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