Advances in aircraft and spacecraft science

  • 제3권4호
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  • Pages.367-378
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  • 2016
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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A numerical method for the study of fluidic thrust-vectoring

  • Ferlauto, Michele (Department of Mechanical and Aerospace Engineering, Politecnico di Torino) ;
  • Marsilio, Roberto (Department of Mechanical and Aerospace Engineering, Politecnico di Torino)
  • 투고 : 2015.09.09
  • 심사 : 2015.11.25
  • 발행 : 2016.10.25
⟨ 이전 논문 다음 논문 ⟩

초록

Thrust Vectoring is a dynamic feature that offers many benefits in terms of maneuverability and control effectiveness. Thrust vectoring capabilities make the satisfaction of take-off and landing requirements easier. Moreover, it can be a valuable control effector at low dynamic pressures, where traditional aerodynamic controls are less effective. A numerical investigation of Fluidic Thrust Vectoring (FTV) is completed to evaluate the use of fluidic injection to manipulate flow separation and cause thrust vectoring of the primary jet thrust. The methodology presented is general and can be used to study different techniques of fluidic thrust vectoring like shock-vector control, sonic-plane skewing and counterflow methods. For validation purposes the method will focus on the dual-throat nozzle concept. Internal nozzle performances and thrust vector angles were computed for several range of nozzle pressure ratios and fluidic injection flow rate. The numerical results obtained are compared with the analogues experimental data reported in the scientific literature. The model is integrated using a finite volume discretization of the compressible URANS equations coupled with a Spalart-Allmaras turbulence model. Second order accuracy in space and time is achieved using an ENO scheme.

키워드

참고문헌

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피인용 문헌

  1. Numerical Investigation of the Dynamic Characteristics of a Dual-Throat-Nozzle for Fluidic Thrust-Vectoring vol.55, pp.1, 2017, https://doi.org/10.2514/1.J055044
  2. Numerical Simulation of Fluidic Thrust-Vectoring vol.95, pp.3, 2016, https://doi.org/10.1007/bf03404724
  3. Optimal aerodynamic design of hypersonic inlets by using streamline-tracing techniques vol.7, pp.5, 2020, https://doi.org/10.12989/aas.2020.7.5.441