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Hinge Method For CFD and Fluid-Ablation Interaction Modeling

Producción científica: Conference contributionrevisión exhaustiva

1 Cita (Scopus)

Resumen

A new method developed for immersed boundary problems is presented. With this method, the fluxes through the computational faces are controlled using a so-called “hinge” matrix. The method is simple to implement and is comparable in accuracy to other immersed boundary methods, such as the Cartesian grid method. However, by using the hinge matrix to control the fluxes, complex interpolations are avoided. The Hinge method is verified by solving a low-speed flow in an irregular domain. The verification indicates that spatial accuracy is maintained even when a coarse mesh is used. The method is then applied to multiple CFD problems including flow through obstacles and high-speed channel flow. To further demonstrate the potential, the developed method is then applied to study the conjugate heat transfer, solid sublimation in fluid, and hypersonic fluid-ablation interaction modeling. Numerous applications are presented to show the great potentials of this new method. Results also show that the proposed method provides a convenient way to model general CFD problems without extensive meshing.

Idioma originalEnglish
Título de la publicación alojadaAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
DOI
EstadoPublished - 2021
EventoAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021 - Virtual, Online
Duración: ago 2 2021ago 6 2021

Serie de la publicación

NombreAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021

Conference

ConferenceAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
CiudadVirtual, Online
Período8/2/218/6/21

Nota bibliográfica

Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Financiación

Financial support for this work was provided by The National Aeronautics and Space Administration Space Technology Research, Development, Demonstration, and Infusion (NASA SpaceTech-REDDI) Award 80NSSC18K0261 and Air Force of Office of Scientific Research 2020 (AFOSR) FA9550-18-1-0261.

FinanciadoresNúmero del financiador
National Aeronautics and Space Administration80NSSC18K0261
Air Force Office of Scientific Research, United States Air ForceFA9550-18-1-0261

    ASJC Scopus subject areas

    • Aerospace Engineering
    • Energy Engineering and Power Technology
    • Nuclear Energy and Engineering

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