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Computational investigation of both geometric and fluidic compressible turbulent thrust vectoring, using a coanda based nozzle

Nayebi, A ; Sharif University of Technology | 2024

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  1. Type of Document: Article
  2. DOI: 10.1063/5.0222070
  3. Publisher: 2024
  4. Abstract:
  5. This study addresses the challenge of enhancing aircraft maneuverability, particularly for vertical landing and takeoff, focusing on the fluidic aerial Coanda high efficiency orienting jet nozzle that employs the Coanda effect to achieve thrust vectoring. This research advances understanding of the interplay between geometric and fluidic factors in thrust vectoring. Stationary, turbulent, and compressible flow conditions are assumed, employing Favre-averaged Reynolds-averaged Navier-Stokes approach with the standard k-ϵ model. Computational solutions were obtained using a pressure-based finite volume method and a structured computational grid. The key findings include thrust vectoring enhancement due to an increase in the total mass flow rate, septum position (at no shock wave-related issues), and Reynolds number. In addition, shock wave formation (at specific mass flow rates and septum positions) considerably affects thrust vectoring. These insights are crucial for optimizing Coanda-based nozzle design in advanced propulsion systems, including in unmanned aircraft vehicles. © 2024 Author(s)
  6. Keywords:
  7. Compressible flow ; Maneuverability ; Navier Stokes equations ; Nozzle design ; Reynolds number ; Rocket nozzles ; Turbulent flow ; Unmanned aerial vehicles (UAV) ; Vortex flow ; Aircraft maneuverability ; Coanda effects ; Computational investigation ; Higher efficiency ; Jet nozzle ; Mass-flow rate ; Shock-waves ; Thrust vectoring ; Vertical landing ; Vertical take-off ; Finite volume method
  8. Source: Physics of Fluids ; Volume 36, Issue 9 , 2024 ; 10706631 (ISSN)
  9. URL: https://pubs.aip.org/aip/pof/article-abstract/36/9/095151/3313306/Computational-investigation-of-both-geometric-and?redirectedFrom=PDF