Comparison of Supercritical and Conventional Wing Flutter Characteristics

Farmer, M. G.; Hanson, P. W.

doi:10.2514/6.1976-1560

Cited by 39 publications

(4 citation statements)

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“…Figures 19 and 20 show flutter speed and corresponding frequency with respect to time before landing. Flutter speed, which gradually decreases in time, takes a dip around transonic Mach numbers, a phenomenon similar to that observed for advanced transport aircraft [28,29]. Also, a variation in x α has effects mostly near the transonic regime, showing that the vehicle is less stable when the mass center is closer to the pitching axis.…”

Section: B Demonstration For Next-generation Hypersonic Transportsupporting

confidence: 63%

Dynamic Stability Analysis of Hypersonic Transport During Reentry

Guruswamy

2016

AIAA Journal

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Dynamic stability analysis is performed for a typical future hypersonic transport vehicle during atmospheric flight. Unsteady aerodynamic data in the form of indicial responses are generated by solving the Navier-Stokes equations. Computations needed at multiple Mach numbers and associated angles of attack are computed in a single job by using dual-level parallel script. Validity of the indicial approach is established by comparing results with experiment and the time-integration method. Flutter boundaries associated with pitch and heave rigid-body degrees of freedom are computed. Effect of position of the mass center on flutter boundaries, which is more predominant in the transonic regime, is shown. This work advances stability analysis procedures for next-generation hypersonic vehicles. Nomenclature

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Section: B Demonstration For Next-generation Hypersonic Transportsupporting

confidence: 63%

Dynamic Stability Analysis of Hypersonic Transport During Reentry

Guruswamy

2016

AIAA Journal

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“…When a wing in transonic flow deforms, shocks move over the surface of the wing [3], which leads to complex aeroelasticity phenomena. An example of such intricate transonic flutter behavior is the transonic dip, which has been observed and described in detail by many researchers [4][5][6]. It is also commonly accepted that linear flutter theories cannot capture this transonic dip behavior accurately [7][8][9].…”

Section: N -mentioning

confidence: 99%

Influence of Transonic Flutter on the Conceptual Design of Next-Generation Transport Aircraft

2019

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Transonic aeroelasticity is an important consideration in the conceptual design of nextgeneration aircraft configurations. This paper develops a low-order physics-based flutter model for swept high-aspect-ratio wings. The approach builds upon a previously developed flutter model that uses the flowfield's lowest moments of vorticity and volume-source density perturbations as its states. The contribution of this paper is a new formulation of the model for swept high-aspect-ratio wings. The aerodynamic model is calibrated using off-line 2D unsteady transonic CFD simulations. Combining that aerodynamic model with a beam model results in a low-dimensional overall aeroelastic system. The low computational cost of the model permits its incorporation in a conceptual design tool for next-generation transport aircraft. The model's capabilities are demonstrated by finding transonic flutter boundaries for different clamped wing configurations, and investigating the influence of transonic flutter on the planform design of next-generation transport aircraft.

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“…4 Another interesting phenomenon that occurs in transonic flows is the transonic dip in the flutter boundary. [5][6][7][8] Linear theories cannot predict the location or shape of the transonic dip, and tend to produce optimistic estimates for the flutter boundary. 9 The seminal work by Theodorsen 10 is widely used for incompressible flutter predictions for two-dimensional airfoils.…”

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confidence: 99%