Hypersonic Fluid–Structure Interaction on a Cantilevered Plate with Shock Impingement. Currao, G. M. D., Neely, A. J., Kennell, C. M., Gai, S. L., & Buttsworth, D. R. AIAA Journal, 57(11):4819–4834, 2019. doi abstract bibtex This work is focused on a hypersonic aeroelastic experiment involving a shock impinging on compliant cantilevered plate at Mach 5.8. The shock induces a pressure differential across the plate thickness that drives its oscillatory behavior. Transition takes place within the separated region, resulting in a fully turbulent boundary layer at the reattachment point, in agreement with previous relevant work. A schlieren system and pressure-sensitive paint are used to measure structural displacement and pressure distribution, respectively. For small deflections, transition results in peak pressure values 15% greater than twoway predictions based on unsteady Reynolds-averaged Navier–Stokes (RANS) equations. Peak pressure evolution is predicted with the piston theory with good accuracy. The reference enthalpy method is corrected on the basis of the Reynolds-averaged Navier–Stokes solution, and it is used to estimate the heat-flux distribution downstream of the reattachment point. Görtler-like vortices are observed and measured in the reattachment region, and their magnitude is affected by the plate deflection. Large trailing-edge displacements result in a smaller streamline curvature at the reattachment point and, consequently, in smaller vortices. Finally, the data are used to predict the performance of two-dimensional control surfaces using the conceptual equivalence of oblique shock-wave/boundary-layer interaction and compression corners. This work aims to establish the accuracy of RANS simulations and low-fidelity models in the reconstruction of the peak heating and peak pressure evolution to bridge ground-testing and real-flight conditions in terms of flap-efficiency predictions and to design an experiment that can be simulated using computationally inexpensive two-dimensional solvers.
@article{currao2019,
title = {Hypersonic {Fluid}–{Structure} {Interaction} on a {Cantilevered} {Plate} with {Shock} {Impingement}},
volume = {57},
issn = {0001-1452},
doi = {10.2514/1.J058375},
abstract = {This work is focused on a hypersonic aeroelastic experiment involving a shock impinging on compliant cantilevered plate at Mach 5.8. The shock induces a pressure differential across the plate thickness that drives its oscillatory behavior. Transition takes place within the separated region, resulting in a fully turbulent boundary layer at the reattachment point, in agreement with previous relevant work. A schlieren system and pressure-sensitive paint are used to measure structural displacement and pressure distribution, respectively. For small deflections, transition results in peak pressure values 15\% greater than twoway predictions based on unsteady Reynolds-averaged Navier–Stokes (RANS) equations. Peak pressure evolution is predicted with the piston theory with good accuracy. The reference enthalpy method is corrected on the basis of the Reynolds-averaged Navier–Stokes solution, and it is used to estimate the heat-flux distribution downstream of the reattachment point. Görtler-like vortices are observed and measured in the reattachment region, and their magnitude is affected by the plate deflection. Large trailing-edge displacements result in a smaller streamline curvature at the reattachment point and, consequently, in smaller vortices. Finally, the data are used to predict the performance of two-dimensional control surfaces using the conceptual equivalence of oblique shock-wave/boundary-layer interaction and compression corners. This work aims to establish the accuracy of RANS simulations and low-fidelity models in the reconstruction of the peak heating and peak pressure evolution to bridge ground-testing and real-flight conditions in terms of flap-efficiency predictions and to design an experiment that can be simulated using computationally inexpensive two-dimensional solvers.},
number = {11},
urldate = {2023-08-03},
journal = {AIAA Journal},
author = {Currao, Gaetano M. D. and Neely, Andrew J. and Kennell, Christopher M. and Gai, Sudhir L. and Buttsworth, David R.},
year = {2019},
pages = {4819--4834},
}
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A schlieren system and pressure-sensitive paint are used to measure structural displacement and pressure distribution, respectively. For small deflections, transition results in peak pressure values 15% greater than twoway predictions based on unsteady Reynolds-averaged Navier–Stokes (RANS) equations. Peak pressure evolution is predicted with the piston theory with good accuracy. The reference enthalpy method is corrected on the basis of the Reynolds-averaged Navier–Stokes solution, and it is used to estimate the heat-flux distribution downstream of the reattachment point. Görtler-like vortices are observed and measured in the reattachment region, and their magnitude is affected by the plate deflection. Large trailing-edge displacements result in a smaller streamline curvature at the reattachment point and, consequently, in smaller vortices. Finally, the data are used to predict the performance of two-dimensional control surfaces using the conceptual equivalence of oblique shock-wave/boundary-layer interaction and compression corners. 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The shock induces a pressure differential across the plate thickness that drives its oscillatory behavior. Transition takes place within the separated region, resulting in a fully turbulent boundary layer at the reattachment point, in agreement with previous relevant work. A schlieren system and pressure-sensitive paint are used to measure structural displacement and pressure distribution, respectively. For small deflections, transition results in peak pressure values 15\\% greater than twoway predictions based on unsteady Reynolds-averaged Navier–Stokes (RANS) equations. Peak pressure evolution is predicted with the piston theory with good accuracy. The reference enthalpy method is corrected on the basis of the Reynolds-averaged Navier–Stokes solution, and it is used to estimate the heat-flux distribution downstream of the reattachment point. Görtler-like vortices are observed and measured in the reattachment region, and their magnitude is affected by the plate deflection. Large trailing-edge displacements result in a smaller streamline curvature at the reattachment point and, consequently, in smaller vortices. Finally, the data are used to predict the performance of two-dimensional control surfaces using the conceptual equivalence of oblique shock-wave/boundary-layer interaction and compression corners. This work aims to establish the accuracy of RANS simulations and low-fidelity models in the reconstruction of the peak heating and peak pressure evolution to bridge ground-testing and real-flight conditions in terms of flap-efficiency predictions and to design an experiment that can be simulated using computationally inexpensive two-dimensional solvers.},\n\tnumber = {11},\n\turldate = {2023-08-03},\n\tjournal = {AIAA Journal},\n\tauthor = {Currao, Gaetano M. D. and Neely, Andrew J. and Kennell, Christopher M. and Gai, Sudhir L. and Buttsworth, David R.},\n\tyear = {2019},\n\tpages = {4819--4834},\n}\n\n\n\n\n\n\n\n\n\n\n\n","author_short":["Currao, G. 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