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Static internal performance of an axisymmetric nozzle with multiaxis thrust-vectoring capability
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1991
Year
AeroacousticsEngineeringFluid MechanicsMechanical EngineeringAerospace SystemNozzle PressureIn-cylinder FlowStatic Test FacilityMultiaxis Thrust-vectoring CapabilityRocket EngineLangley 16Aerospace Propulsion SystemsPropulsionAxisymmetric NozzleAerospace EngineeringMechanical SystemsStatic Internal PerformanceAerodynamicsAerospace PropulsionNozzle Aerodynamics
An investigation was conducted in the static test facility of the Langley 16 Foot Transonic Tunnel in order to determine the internal performance characteristics of a multiaxis thrust vectoring axisymmetric nozzle. Thrust vectoring for this nozzle was achieved by deflection of only the divergent section of this nozzle. The effects of nozzle power setting and divergent flap length were studied at nozzle deflection angles of 0 to 30 at nozzle pressure ratios up to 8.0.