Efficient Treatment of Structural Deformation for Aerothermoelastic Loads Prediction in High-Speed Flows. Brouwer, K., R., Gogulapati, A., & Mcnamara, J., J. In 15th Dynamics Specialists Conference, 2016. ![Efficient Treatment of Structural Deformation for Aerothermoelastic Loads Prediction in High-Speed Flows [pdf]](https://bibbase.org/img/filetypes/pdf.svg "pdf")
Paper doi abstract bibtex Accurate and efficient prediction of aerodynamic loads for lightweight aerospace systems is critical to the development of modern reusable high-speed platforms. This is particularly challenging to achieve for structures that exhibit higher order local deformations which, when coupled with invsicid-viscous interactions and non-isentropic flow, can lead to significant local variations in the aerodynamic loads. This study is focused on comparing two strategies for computing aerodynamic pressure loads in order to identify an accurate and efficient approach that requires minimal a priori assumptions regarding the structural response. The first strategy relies on parameterization of the structure in terms of a set of characteristic shapes. The characteristic shapes are identified by exciting the structure of interest using a representative load and then extracting the dominant features of the response. The set of characteristic shapes are then used to generate fluid loads from a Reynold's Averaged Navier-Stokes solution. The second strategy relies on approximate fluid models to compute the aerodynamic pressure. The approximate models considered as part of this study include classical piston theory, a local piston theory method where relevant freestream parameters are replaced by spatially local quantities , and an inviscid-viscous interaction model that attempts to account for the presence of the viscous boundary layer over a deformed surface. The various approaches are compared against Reynold's Averaged Navier-Stokes solutions in the context of a two-dimensional compliant panel subject to shock impingement. The results of this study indicate the following: 1) Accurate and efficient parameteriza-tion of the structure using characteristic shapes is possible, assuming that representative loads are used to excite the structure, 2) The pressure is relatively insensitive to reconstruction errors of structural displacements fit to a truncated set of modes, and 3) Approximate fluid models are capable of reasonably accurate and efficient prediction of pressure loads for a compliant panel subject to shock impingement. Nomenclature A Amplitude a Speed of sound C Covariance matrix C f Coefficient of skin friction c Constant D Flexural stiffness E Young's Modulus f Frequency H Boundary layer shape factor h Panel thickness L Panel length M Mach number m Total number of nodes in each snapshot N Total number of snapshots P Fluid pressure P N oise White noise pressure load
@inproceedings{
title = {Efficient Treatment of Structural Deformation for Aerothermoelastic Loads Prediction in High-Speed Flows},
type = {inproceedings},
year = {2016},
city = {San Diego, CA},
id = {440560b1-04c6-362f-9b4c-5e21531e3bc9},
created = {2021-02-17T23:55:36.110Z},
accessed = {2021-02-17},
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abstract = {Accurate and efficient prediction of aerodynamic loads for lightweight aerospace systems is critical to the development of modern reusable high-speed platforms. This is particularly challenging to achieve for structures that exhibit higher order local deformations which, when coupled with invsicid-viscous interactions and non-isentropic flow, can lead to significant local variations in the aerodynamic loads. This study is focused on comparing two strategies for computing aerodynamic pressure loads in order to identify an accurate and efficient approach that requires minimal a priori assumptions regarding the structural response. The first strategy relies on parameterization of the structure in terms of a set of characteristic shapes. The characteristic shapes are identified by exciting the structure of interest using a representative load and then extracting the dominant features of the response. The set of characteristic shapes are then used to generate fluid loads from a Reynold's Averaged Navier-Stokes solution. The second strategy relies on approximate fluid models to compute the aerodynamic pressure. The approximate models considered as part of this study include classical piston theory, a local piston theory method where relevant freestream parameters are replaced by spatially local quantities , and an inviscid-viscous interaction model that attempts to account for the presence of the viscous boundary layer over a deformed surface. The various approaches are compared against Reynold's Averaged Navier-Stokes solutions in the context of a two-dimensional compliant panel subject to shock impingement. The results of this study indicate the following: 1) Accurate and efficient parameteriza-tion of the structure using characteristic shapes is possible, assuming that representative loads are used to excite the structure, 2) The pressure is relatively insensitive to reconstruction errors of structural displacements fit to a truncated set of modes, and 3) Approximate fluid models are capable of reasonably accurate and efficient prediction of pressure loads for a compliant panel subject to shock impingement. Nomenclature A Amplitude a Speed of sound C Covariance matrix C f Coefficient of skin friction c Constant D Flexural stiffness E Young's Modulus f Frequency H Boundary layer shape factor h Panel thickness L Panel length M Mach number m Total number of nodes in each snapshot N Total number of snapshots P Fluid pressure P N oise White noise pressure load},
bibtype = {inproceedings},
author = {Brouwer, Kirk R and Gogulapati, Abhijit and Mcnamara, Jack J},
doi = {10.2514/6.2016-1089},
booktitle = {15th Dynamics Specialists Conference}
}
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The approximate models considered as part of this study include classical piston theory, a local piston theory method where relevant freestream parameters are replaced by spatially local quantities , and an inviscid-viscous interaction model that attempts to account for the presence of the viscous boundary layer over a deformed surface. The various approaches are compared against Reynold's Averaged Navier-Stokes solutions in the context of a two-dimensional compliant panel subject to shock impingement. 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