Hypersonic Fluid-Structure Interaction on a Cantilevered Plate. Currao, G., Neely, A., Robert Buttsworth, D., & Gai, S. In 7th European Conference for Aeronautics and Space Sciences (EUCASS), 2017. ![Hypersonic Fluid-Structure Interaction on a Cantilevered Plate [pdf]](https://bibbase.org/img/filetypes/pdf.svg "pdf")
Paper ![Hypersonic Fluid-Structure Interaction on a Cantilevered Plate [link]](https://bibbase.org/img/filetypes/link.svg "link")
Website doi abstract bibtex This work is a numerical and experimental study of fluid-structure interaction at Mach 5.8. Numerical results from low-and high-fidelity models are shown and compared. Procedures and details of the generation of the numerical mesh are given. The mesh topology shape, irrespective of flow direction, shock position, and sonic line location can lead to non-physical results if not optimised. Orthogonality of the cells to the wall is fundamentally important to reach numerical convergence and reliable results. Under an inviscid point of view, piston theory is confirmed to be an appropriate tool in the evaluation of the inviscid pressure over the plate, as it showed good agreement with the empirical data. Concerning the viscous aspects, the shear stress and heat transfer histories shared the same frequency with the structural, and their spatial distribution present a degree for hysteresis. Finally, the boundary layer height changes not only according to local slope and speed of the wall, but it is a function of the actual structural mode of vibration. Nomenclature Flow Variables: q = Heat flux rate on the plate p = Pressure τ = Shear stress on the plate a = Sound speed St = Stanton number Cf = Skin friction coefficient M = Mach number Structural Variables l = Beam element's length L = Plate length T = Period of oscillation th = Plate's thickness w = Structural displacement θ = Local slope ω = Frequency (= 2πf) E = Young's modulus I = Inertia of the beam cross-section M = Mass matrix K = Stiffness matrix D ̅ = Damping matrix ζ = Damping ratio α,β = Rayleigh coefficients Other Variables x = Coordinate tangent to the wall y = Coordinate normal to the wall t = Time η = Ratio between pressure with 3D effects and 2D pressure Subscripts: w = At the wall S = Structure 1 = 1 st mode 2 = Post-shock conditions or 2 nd mode 3 = 3 rd mode ∞ = Freestream conditions Abbreviations: BL = Boundary layer LE = Leading edge PT1= Pressure transducer near the hinge line PT2= Pressure transducer near the trailing edge PT3= Pressure transducer beneath the plate TE = Trailing edge TUSQ = Wind tunnel at University of Southern Queensland
@inproceedings{
title = {Hypersonic Fluid-Structure Interaction on a Cantilevered Plate},
type = {inproceedings},
year = {2017},
websites = {https://www.researchgate.net/publication/320087702},
id = {927afa35-2ba5-35ce-8285-c1e9694bd466},
created = {2021-10-26T22:11:07.288Z},
accessed = {2021-10-26},
file_attached = {true},
profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},
group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},
last_modified = {2021-10-26T22:11:07.874Z},
read = {false},
starred = {false},
authored = {false},
confirmed = {false},
hidden = {false},
citation_key = {currao:eucass:2017},
private_publication = {false},
abstract = {This work is a numerical and experimental study of fluid-structure interaction at Mach 5.8. Numerical results from low-and high-fidelity models are shown and compared. Procedures and details of the generation of the numerical mesh are given. The mesh topology shape, irrespective of flow direction, shock position, and sonic line location can lead to non-physical results if not optimised. Orthogonality of the cells to the wall is fundamentally important to reach numerical convergence and reliable results. Under an inviscid point of view, piston theory is confirmed to be an appropriate tool in the evaluation of the inviscid pressure over the plate, as it showed good agreement with the empirical data. Concerning the viscous aspects, the shear stress and heat transfer histories shared the same frequency with the structural, and their spatial distribution present a degree for hysteresis. Finally, the boundary layer height changes not only according to local slope and speed of the wall, but it is a function of the actual structural mode of vibration. Nomenclature Flow Variables: q = Heat flux rate on the plate p = Pressure τ = Shear stress on the plate a = Sound speed St = Stanton number Cf = Skin friction coefficient M = Mach number Structural Variables l = Beam element's length L = Plate length T = Period of oscillation th = Plate's thickness w = Structural displacement θ = Local slope ω = Frequency (= 2πf) E = Young's modulus I = Inertia of the beam cross-section M = Mass matrix K = Stiffness matrix D ̅ = Damping matrix ζ = Damping ratio α,β = Rayleigh coefficients Other Variables x = Coordinate tangent to the wall y = Coordinate normal to the wall t = Time η = Ratio between pressure with 3D effects and 2D pressure Subscripts: w = At the wall S = Structure 1 = 1 st mode 2 = Post-shock conditions or 2 nd mode 3 = 3 rd mode ∞ = Freestream conditions Abbreviations: BL = Boundary layer LE = Leading edge PT1= Pressure transducer near the hinge line PT2= Pressure transducer near the trailing edge PT3= Pressure transducer beneath the plate TE = Trailing edge TUSQ = Wind tunnel at University of Southern Queensland},
bibtype = {inproceedings},
author = {Currao, Gaetano and Neely, Andrew and Robert Buttsworth, David and Gai, S.},
doi = {10.13009/EUCASS2017-299},
booktitle = {7th European Conference for Aeronautics and Space Sciences (EUCASS)}
}
Downloads: 0
{"_id":"k48A9CpQhuc5ZudBS","bibbaseid":"currao-neely-robertbuttsworth-gai-hypersonicfluidstructureinteractiononacantileveredplate-2017","author_short":["Currao, G.","Neely, A.","Robert Buttsworth, D.","Gai, S."],"bibdata":{"title":"Hypersonic Fluid-Structure Interaction on a Cantilevered Plate","type":"inproceedings","year":"2017","websites":"https://www.researchgate.net/publication/320087702","id":"927afa35-2ba5-35ce-8285-c1e9694bd466","created":"2021-10-26T22:11:07.288Z","accessed":"2021-10-26","file_attached":"true","profile_id":"6476e386-2170-33cc-8f65-4c12ee0052f0","group_id":"5a9f751c-3662-3c8e-b55d-a8b85890ce20","last_modified":"2021-10-26T22:11:07.874Z","read":false,"starred":false,"authored":false,"confirmed":false,"hidden":false,"citation_key":"currao:eucass:2017","private_publication":false,"abstract":"This work is a numerical and experimental study of fluid-structure interaction at Mach 5.8. Numerical results from low-and high-fidelity models are shown and compared. Procedures and details of the generation of the numerical mesh are given. The mesh topology shape, irrespective of flow direction, shock position, and sonic line location can lead to non-physical results if not optimised. Orthogonality of the cells to the wall is fundamentally important to reach numerical convergence and reliable results. Under an inviscid point of view, piston theory is confirmed to be an appropriate tool in the evaluation of the inviscid pressure over the plate, as it showed good agreement with the empirical data. Concerning the viscous aspects, the shear stress and heat transfer histories shared the same frequency with the structural, and their spatial distribution present a degree for hysteresis. Finally, the boundary layer height changes not only according to local slope and speed of the wall, but it is a function of the actual structural mode of vibration. Nomenclature Flow Variables: q = Heat flux rate on the plate p = Pressure τ = Shear stress on the plate a = Sound speed St = Stanton number Cf = Skin friction coefficient M = Mach number Structural Variables l = Beam element's length L = Plate length T = Period of oscillation th = Plate's thickness w = Structural displacement θ = Local slope ω = Frequency (= 2πf) E = Young's modulus I = Inertia of the beam cross-section M = Mass matrix K = Stiffness matrix D ̅ = Damping matrix ζ = Damping ratio α,β = Rayleigh coefficients Other Variables x = Coordinate tangent to the wall y = Coordinate normal to the wall t = Time η = Ratio between pressure with 3D effects and 2D pressure Subscripts: w = At the wall S = Structure 1 = 1 st mode 2 = Post-shock conditions or 2 nd mode 3 = 3 rd mode ∞ = Freestream conditions Abbreviations: BL = Boundary layer LE = Leading edge PT1= Pressure transducer near the hinge line PT2= Pressure transducer near the trailing edge PT3= Pressure transducer beneath the plate TE = Trailing edge TUSQ = Wind tunnel at University of Southern Queensland","bibtype":"inproceedings","author":"Currao, Gaetano and Neely, Andrew and Robert Buttsworth, David and Gai, S.","doi":"10.13009/EUCASS2017-299","booktitle":"7th European Conference for Aeronautics and Space Sciences (EUCASS)","bibtex":"@inproceedings{\n title = {Hypersonic Fluid-Structure Interaction on a Cantilevered Plate},\n type = {inproceedings},\n year = {2017},\n websites = {https://www.researchgate.net/publication/320087702},\n id = {927afa35-2ba5-35ce-8285-c1e9694bd466},\n created = {2021-10-26T22:11:07.288Z},\n accessed = {2021-10-26},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-26T22:11:07.874Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {currao:eucass:2017},\n private_publication = {false},\n abstract = {This work is a numerical and experimental study of fluid-structure interaction at Mach 5.8. Numerical results from low-and high-fidelity models are shown and compared. Procedures and details of the generation of the numerical mesh are given. The mesh topology shape, irrespective of flow direction, shock position, and sonic line location can lead to non-physical results if not optimised. Orthogonality of the cells to the wall is fundamentally important to reach numerical convergence and reliable results. Under an inviscid point of view, piston theory is confirmed to be an appropriate tool in the evaluation of the inviscid pressure over the plate, as it showed good agreement with the empirical data. Concerning the viscous aspects, the shear stress and heat transfer histories shared the same frequency with the structural, and their spatial distribution present a degree for hysteresis. Finally, the boundary layer height changes not only according to local slope and speed of the wall, but it is a function of the actual structural mode of vibration. Nomenclature Flow Variables: q = Heat flux rate on the plate p = Pressure τ = Shear stress on the plate a = Sound speed St = Stanton number Cf = Skin friction coefficient M = Mach number Structural Variables l = Beam element's length L = Plate length T = Period of oscillation th = Plate's thickness w = Structural displacement θ = Local slope ω = Frequency (= 2πf) E = Young's modulus I = Inertia of the beam cross-section M = Mass matrix K = Stiffness matrix D ̅ = Damping matrix ζ = Damping ratio α,β = Rayleigh coefficients Other Variables x = Coordinate tangent to the wall y = Coordinate normal to the wall t = Time η = Ratio between pressure with 3D effects and 2D pressure Subscripts: w = At the wall S = Structure 1 = 1 st mode 2 = Post-shock conditions or 2 nd mode 3 = 3 rd mode ∞ = Freestream conditions Abbreviations: BL = Boundary layer LE = Leading edge PT1= Pressure transducer near the hinge line PT2= Pressure transducer near the trailing edge PT3= Pressure transducer beneath the plate TE = Trailing edge TUSQ = Wind tunnel at University of Southern Queensland},\n bibtype = {inproceedings},\n author = {Currao, Gaetano and Neely, Andrew and Robert Buttsworth, David and Gai, S.},\n doi = {10.13009/EUCASS2017-299},\n booktitle = {7th European Conference for Aeronautics and Space Sciences (EUCASS)}\n}","author_short":["Currao, G.","Neely, A.","Robert Buttsworth, D.","Gai, S."],"urls":{"Paper":"https://bibbase.org/service/mendeley/6476e386-2170-33cc-8f65-4c12ee0052f0/file/422f574c-a6ba-922f-1390-cfac27240260/full_text.pdf.pdf","Website":"https://www.researchgate.net/publication/320087702"},"biburl":"https://bibbase.org/service/mendeley/6476e386-2170-33cc-8f65-4c12ee0052f0","bibbaseid":"currao-neely-robertbuttsworth-gai-hypersonicfluidstructureinteractiononacantileveredplate-2017","role":"author","metadata":{"authorlinks":{}}},"bibtype":"inproceedings","biburl":"https://bibbase.org/service/mendeley/6476e386-2170-33cc-8f65-4c12ee0052f0","dataSources":["qwkM8ZucCwtxbnXfc","ya2CyA73rpZseyrZ8","2252seNhipfTmjEBQ"],"keywords":[],"search_terms":["hypersonic","fluid","structure","interaction","cantilevered","plate","currao","neely","robert buttsworth","gai"],"title":"Hypersonic Fluid-Structure Interaction on a Cantilevered Plate","year":2017}