A System Study On Fluidic Thrust Vectoring

Pelt, Hilbert Van; Neely, Andrew J.; Young, John

doi:10.2514/6.2015-3565

Cited by 7 publications

(2 citation statements)

References 9 publications

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“…The experimental model was designed as a 2D generic scramjet shape, following a similar geometry to Van Pelt et al (2017). The dual-ramp intake compresses the freestream flow before expanding it through a 19 degree straight-sided nozzle.…”

Section: Experimental Modelmentioning

confidence: 99%

Investigation of fluidic thrust vectoring for scramjets

et al. 2023

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Fluidic thrust vectoring (FTV) offers a novel approach to aerodynamic control, circumventing some of the issues associated with mechanical systems. One method is shock vector control which involves injecting a fluid into the exhaust nozzle of an engine to redirect the gases and thus, produce a control force. An experimental model which incorporated FTV was designed and tested at Mach 6 in the Oxford high density tunnel (HDT). The model was a simplified two-dimensional scramjet geometry with two different configurations to compare an internal and external exhaust nozzle. The FTV injection system consisted of a slot at the rear edge of the exhaust nozzle fed from an internal plenum. In the experimental campaign, a range of gas injection pressures and free stream stagnation pressures were tested to assess the effectiveness of both configurations. Two new measurement methods were successfully implemented in the HDT: pressure sensitive paint and a 6-axis load cell. The FTV system has been shown to be effective with observable increases in lift and pitching moment. A linear relation between the injection pressure ratio and the control forces could be observed for both configurations. Graphical abstract

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Section: Experimental Modelmentioning

confidence: 99%

Investigation of fluidic thrust vectoring for scramjets

et al. 2023

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“…Moreover, it can be implemented with the minimum penalty of the aircraft observability. 3 Because of these advantages, several approaches to fluidic thrust-vectoring have been proposed in the past years, including Coanda effect by use of coflow blowing and counter-flow aspiration 4,5 shock vector control, [6][7][8][9][10] throat-skewing 11 and Dual-Throat Nozzle (DTN) configuration. 2,12,13 Among these, the DTN configuration has shown to achieve greater thrust vectoring efficiency, without compromising the axial component of thrust.…”

Section: Introductionmentioning

confidence: 99%

Numerical study of secondary mass flow modulation in a Bypass Dual-Throat Nozzle

Hamedi-Estakhrsar

Ferlauto

Mahdavy-Moghaddam

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The fluidic thrust-vectoring modulation on a Bypass Dual-Throat Nozzle (BDTN) is studied numerically. The thrust vectoring modulation is obtained by varying the secondary mass flow, introducing different area contraction ratios of the bypass duct. The scope of present study is twofold: (i) to set up a model for the control of the secondary mass flow that is consistent with the resolution of the nozzle main flow and (ii) to derive a simplified representation of a valve system embedded in the bypass channel. The simulations of the turbulent airflow inside the BDTN and its efflux in the external ambient have been simulated by using RANS approach with RNG [Formula: see text] turbulence modeling. The numerical results have been validated with experimental and numerical data available in the open literature. The nozzle performance and thrust vector angle are computed for different values of the bypass area contraction ratio. The effects of different secondary mass flow rates on the system resultant thrust ratio and discharge coefficient of the bypass dual-throat nozzle have been investigated. By using the proposed approach to the secondary mass flow modulation, the thrust pitch angle has been controlled up to 27°.

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