Experimental and numerical research of a supersonic planar thrust vectoring nozzle via mechanical tabs
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چکیده
منابع مشابه
Analytical and Experimental Evaluation of Aerodynamic Thrust Vectoring on an Aerospike Nozzle
Results from numerical and coldow experimental investigations of aerodynamic thrust vectoring on a small-scale aerospike thruster are presented. Thrust vectoring was created by the injection of a secondary uid into the primary ow eld normal to the nozzle axis. The experimental aerospike nozzle was truncated at 57% of its full theoretical length. Data derived from coldow thrust vectoring tests w...
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Traditional mechanical control systems in thrust vectoring are efficient in rocket thrust guidance but their costs and their weights are excessive. The fluidic injection in the nozzle divergent constitutes an alternative procedure to achieve the goal. In this paper, we present a 3D analytical model for fluidic injection in a supersonic nozzle integrating an orifice. The fluidic vectoring uses a...
متن کاملNumerical Studies on Thrust Vectoring Using Shock Induced Supersonic Secondary Jet
Numerical studies have been carried out using a validated two-dimensional RNG k-epsilon turbulence model for the design optimization of a thrust vector control system using shock induced supersonic secondary jet. Parametric analytical studies have been carried out with various secondary jets at different divergent locations, jet interaction angles, jet pressures. The results from the parametric...
متن کاملNumerical Investigation of Supersonic Nozzle Flow Separation
S EPARATION of supersonic flow in a convergent–divergent nozzle is a fundamental fluid phenomenon that affects a large variety of applications, from fuel systems to aircraft engine nozzles. When a supersonic nozzle is operated at pressure ratioswell below its design point, a shock forms inside the nozzle andflowdownstreamof the shock separates from the nozzle walls. Even though flow separation ...
متن کاملDesign of a Small Scale Aerospike Nozzle and Associated Testing Infrastructure for Experimental Evaluation of Aerodynamic Thrust Vectoring
A system for cold ow testing of an aerospike nozzle has been developed in an e ort to examine the e ectiveness of aerodynamic thrust vectoring and truncated nozzle base bleed. These tests are designed to produce results that will support the design of a system for hot ow testing of the same technologies. Design of a nozzle suitable for testing with reasonable cold-gas mass ow rates and measurea...
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ژورنال
عنوان ژورنال: FME Transaction
سال: 2014
ISSN: 1451-2092
DOI: 10.5937/fmet1403205z