Model Reduction of Computational Aerothermodynamics for Hypersonic Aerothermoelasticity

Crowell, Andrew; McNamara, Jack J.

doi:10.2514/1.j051094

Cited by 72 publications

(50 citation statements)

References 22 publications

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“…However, piston theory enjoyed renewed attention in the 1990s, with the early implementation of piston theory with Euler solutions in CFD [8] and with continued development of aeroelastic panel codes [9]. The 2000s saw a marked resurgence in the interest in piston theory as a computationally inexpensive method for modelling supersonic and hypersonic aeroelastic problems, with applications being found in aeroservo-elasticity and aero-thermo-elasticity, with the further integration of piston theory with CFD; recent literature highlights the continued application of piston theory in reducing the computational cost of CFD for hypersonic aeroelasticity [10][11][12][13][14][15].…”

mentioning

confidence: 99%

Generalized Formulation and Review of Piston Theory for Airfoils

Meijer

Dala

2016

AIAA Journal

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The present work presents a brief review of some of the notable contributions to piston theory and of its theoretical basis. A generalized formulation of piston theory is given, applicable to both local and classical piston theory. A consistent generalized formulation of the downwash equation is given, accounting for arbitrary motion in the plane of the airfoil. The formulation reduces to established downwash equations through appropriate definition of the cylinder orientation. The theoretical range of validity of Lighthill's classical piston theory is examined, and the relative accuracy of a number of approximate theories encapsulated by the formulation as applied to a planar wedge is considered. The relative importance of higher-order terms in piston theory is examined, with the significance of recent literature extending the fidelity of the firstorder term highlighted. It is subsequently suggested that current implementations of local piston theory may be improved through the use of a first-order term of suitable accuracy.

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confidence: 99%

Generalized Formulation and Review of Piston Theory for Airfoils

Meijer

Dala

2016

AIAA Journal

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“…Typical approaches for model reduction of unsteady, nonlinear flows include proper orthogonal decomposition (POD), [36][37][38] Volterra series, 38,39 and surrogates. [40][41][42][43][44][45] Each of these seek to identify the primary features of a system from a limited number of high-fidelity flow solutions. The generation of this dataset requires an initial computational investment.…”

Section: Development Of a Cfd Surrogate Modelmentioning

confidence: 99%

Modeling and Analysis of Shock Impingements on Thermo-Mechanically Compliant Surface Panels

Miller¹,

Crowell²,

McNamara³

2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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13
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Fluid-Thermal-Structural interactions play an important role in the development of high speed vehicles, impacting various sub-disciplines (i.e., aerodynamic, structural, material, propulsion, and control) at the micro, component and/or vehicle scales. This study focuses on the development of a partitioned fluid-thermal-structural procedure aimed at performing a long time record thermo-structural response prediction of surface panels subject to shock impingements. Specific modeling aspects essential to this are reduction of the computational aerothermodynamics to a tractable model, and partitioned timemarching of the fluid-thermal-structural problem. Additional factors considered are: 1) the movement of the shock impingement due to forced motion of a shock generator, 2) panel backpressure, 3) a 140dB random prescribed pressure load to account for pressure fluctuations associated with turbulent boundary layers, and 4) coupled vs. uncoupled fluid-thermal-structural analysis. Results indicate that quasistatic CFD analysis provides a promising means for generating an aerothermodynamic surrogate model. Differences between quasi-static and unsteady models were under 6% for both panel temperature rise and pressure loads for a forced motion analysis. Several studies using the fluid-thermal-structural model are performed, focusing on the differences between the coupled and uncoupled analyses, as well as the role of backpressure on the panel response. The effect of the backpressure to the direction of panel buckling is investigated, and the backpressure required to buckle the panel into the flow is predicted to be ∼10% of free stream higher for the uncoupled model than the coupled model. However, generally differences were minor between the coupled and uncoupled analysis. The inclusion of a 140 dB prescribed pressure load, meant to mimic the effect of turbulent boundary layer loadings, results in negligible temperature differences. However, both the shock motion and this load introduce large amplitude oscillations at the start of the response, followed by relatively small oscillations once the buckling amplitude of the panel becomes significant.

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“…Whereas the early research was instrumental in providing the basis for the aerothermoelastic design of the X-15 and the space shuttle [3][4][5], the current focus is on the development of hypersonic technologies for next-generation reusable launch vehicles and hypersonic cruise vehicles [6][7][8]. Current research includes: development of reduced order models for aerothermoelastic systems [9,10], structural optimisation [11], uncertainty propagation [12,13], coupling CFD with aerothermoelastic models [14], two-dimensional nonlinear flutter models [15] and three-dimensional flutter models [16]. This work has shown that the dynamic behaviour of the structure under the harsh thermal environment must be investigated for hypersonic aircraft to become a reality.…”

Section: Introductionmentioning
confidence: 99%

Transient Temperature Effects on the Aerothermoelastic Response of a Simple Wing
Vio
¹
,
Munk
²
,
Verstraete
³

2018
Aerospace
2
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1
0
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Aerothermoelasticity plays a vital role in the design and optimisation of hypersonic aircraft. Furthermore, the transient and nonlinear effects of the harsh thermal and aerodynamic environment a lifting surface is in cannot be ignored. This article investigates the effects of transient temperatures on the flutter behavior of a three-dimensional wing with a control surface and compares results for transient and steady-state temperature distributions. The time-varying temperature distribution is applied through the unsteady heat conduction equation coupled to nonlinear aerodynamics calculated using 3rd order piston theory. The effect of a transient temperature distribution on the flutter velocity is investigated and the results are compared with a steady-state heat distribution. The steady-state condition proves to over-compensate the effects of heat on the flutter response, whereas the transient case displays the effects of a constantly changing heat load by varying the response as time progresses.

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Model Reduction of Computational Aerothermodynamics for Hypersonic Aerothermoelasticity

Cited by 72 publications

References 22 publications

Generalized Formulation and Review of Piston Theory for Airfoils

Generalized Formulation and Review of Piston Theory for Airfoils

Modeling and Analysis of Shock Impingements on Thermo-Mechanically Compliant Surface Panels

Transient Temperature Effects on the Aerothermoelastic Response of a Simple Wing

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