Aeroelastic Stability of High-Speed Cylindrical Vehicles

Klock, Ryan J.; Cesnik, Carlos E. S.

doi:10.2514/6.2017-0406

Cited by 5 publications

(3 citation statements)

References 24 publications

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“…The test article used in this study is a simplified, reduced-scale axisymmetric model of the Initial Concept 3.X vehicle (IC3X), which was established by Witeoff and Neergaard [23] using the PASS code suite. This geometry is chosen as it is an operationally relevant yet canonical geometry that is of interest to the hypersonic community.…”

Section: Model Geometrymentioning

confidence: 99%

“…The model geometry chosen (IC3X) is a generic hypersonic vehicle design representing an air-launched vehicle capable of completing a standard three-phase mission trajectory [22]. This geometry is of particular interest to the hypersonic community and has been the focus of multiple studies in the literature in recent years for hypersonic aeroelasticity [18,22,23] and aerothermodynamics [24][25][26]. This paper presents a comprehensive thermal evaluation of the model carried out in the current experimental campaign [27].…”

Section: Introductionmentioning

confidence: 99%

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Thermal Evaluation of the Initial Concept 3.X Vehicle at Mach 7

Dhanagopal,

Strasser,

Andrade

et al. 2024

Energies

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High-speed global surface temperature distributions and heat flux measurements on the Initial Concept 3.X vehicle (IC3X) model were investigated at the UTSA Mach 7 wind tunnel, examining angles of attack of 0° and 5° at a freestream unit Reynolds number (Re) ~7 × 106 m−1. A ruthenium-based, fast-responding, temperature-sensitive paint (fast-TSP) prepared in-house was applied to a 7.1% scale model of the vehicle. Static calibration was performed to convert the intensity measurements into surface temperature values. The surface temperatures and derived heat flux fields conformed to the predicted trends, which was corroborated by Schlieren flow visualization. Notably, the average surface temperature variation was identified to range from 6 to 34 K at a 0° angle of attack and from 11 to 44 K at a 5° angle of attack, with the most pronounced gradient detected at the stagnation point. Additional measurements provided a detailed thermal assessment of the model, including estimations of the stagnation point heat flux, the convective heat transfer coefficient, and the modified Stanton number. Statistical and time series analyses of the data collected revealed the absence of prevailing unsteady phenomena, suggesting that the tested design geometry is well suited for hypersonic flight applications. These experimental outcomes not only shed light on the aerothermodynamics experienced during high-speed flight but also underscore the effectiveness of fast-TSP in capturing both quantitative and qualitative thermal data.

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Section: Model Geometrymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Thermal Evaluation of the Initial Concept 3.X Vehicle at Mach 7

Dhanagopal,

Strasser,

Andrade

et al. 2024

Energies

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“…Alder addressed the effect of a turbulent boundary layer on the supersonic flutter of a circular cylindrical shell by using a high‐fidelity fluid‐structure model in which the MSC Nastran finite element solver was coupled with the Navier‐Stokes solver DLR‐Tau. Klock and Cesnik studied the aeroelastic response of a pressurized circular cylindrical shell subjected to axial flow at Mach 3 using a nonlinear transient FEM on the basis of ABAQUS FEM/CAE software and the third‐order piston theory.…”

Section: Introductionmentioning

confidence: 99%

Sloshing effects on supersonic flutter characteristics of a circular cylindrical shell partially filled with liquid

Zarifian

Ovesy

Firouz-Abadi

2018

Numerical Meth Engineering

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Summary This paper aims to revisit the effect of sloshing on the flutter characteristics of a partially liquid‐filled cylinder. A computational fluid‐structure interaction model within the framework of the finite element method is developed to capture fluid‐structure interactions arising from the sloshing of the internal fluid and the flexibility of its containing structure exposed to an external supersonic airflow. The internal liquid sloshing is represented by a more sophisticated model, referred to as the liquid sloshing model, and the shell structure is modeled by Sanders' shell theory. The aerodynamic pressure loading is approximated by the first‐order piston theory. The initial geometric stiffness due to prestresses in the initial configuration stemming from the fluid hydrostatic pressure, internal pressure, and axial compression load is also considered. The obtained results reveal that the sloshing of the internal fluid has little influence on the supersonic flutter boundary of a cylinder partially filled with liquid, at least for the case considered here. It is also shown that the critical freestream static pressure predicted by the sloshing model is negligibly larger than that calculated by the hydroelastic model of the internal fluid, which means that the sloshing of the internal fluid slightly overestimates the flutter boundary.

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