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Vortex lattice method

About: Vortex lattice method is a research topic. Over the lifetime, 779 publications have been published within this topic receiving 9242 citations.


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Journal ArticleDOI
TL;DR: In this paper, the aeroelastic response and stability of hingeless rotor blades in hover are investigated using both refined structural and aerodynamic models, including compressibility effect and a thin lifting-surface theory based on the unsteady vortex lattice method.
Abstract: The aeroelastic response and stability of hingeless rotor blades in hover are investigated using both refined structural and aerodynamic models. Finite elements based on a large deflection-type beam theory are used for structural analysis. Although the strain components in the beam element are assumed to be small compared to unity, no kinematical limitations are imposed on the magnitude of displacements and rotations. A three-dimensional aerodynamic model including compressibility effect, which is a thin lifting-surface theory based on the unsteady vortex lattice method, is applied to evaluate the aerodynamic loads. A thin lifting-surface and its wake are represented by a number of the quadrilateral vortex-ring elements. The wake geometry is prescribed from the known generalized equations. Numerical results of the steady-state deflections and the stability for the stiff in-plane rotor blade are presented. It is found that the three-dimensional aerodynamic tip-relief, unsteady wake dynamics, and compressibility effects, not predicted in the two-dimensional strip theory, play an important role in the hingeless rotor aeroelastic analysis in hover.

9 citations

Journal ArticleDOI
TL;DR: In this article, a framework of aeroelastic optimization design for high-aspect-ratio wing with large deformation is presented, where parameters of beam cross section are chosen as the design variables to satisfy the displacement, flutter, and strength requirements, while minimizing wing weight.
Abstract: This paper presents a framework of aeroelastic optimization design for high-aspect-ratio wing with large deformation. A highly flexible wing model for wind tunnel test is optimized subjected to multiple aeroelastic constraints. Static aeroelastic analysis is carried out for the beamlike wing model, using a geometrically nonlinear beam formulation coupled with the nonplanar vortex lattice method. The flutter solutions are obtained using the - method based on the static equilibrium configuration. The corresponding unsteady aerodynamic forces are calculated by nonplanar doublet-lattice method. This paper obtains linear and nonlinear aeroelastic optimum results, respectively, by the ISIGHT optimization platform. In this optimization problem, parameters of beam cross section are chosen as the design variables to satisfy the displacement, flutter, and strength requirements, while minimizing wing weight. The results indicate that it is necessary to consider geometrical nonlinearity in aeroelastic optimization design. In addition, optimization strategies are explored to simplify the complex optimization process and reduce the computing time. Different criterion values are selected and studied for judging the effects of the simplified method on the computing time and the accuracy of results. In this way, the computing time is reduced by more than 30% on the premise of ensuring the accuracy.

9 citations

Journal ArticleDOI
TL;DR: In this paper, the aerodynamic and aero-elastic behavior of a 2D wing section with and without flap is analyzed with Theodorsen theory and Unsteady Vortex Lattice Method (low fidelity), Euler (medium fidelity) and Reynolds-Averaged Navier Stokes (high fidelity) methods.

9 citations

Proceedings ArticleDOI
01 Jun 1987
TL;DR: In this paper, a numerical simulation of subsonic aeroelastic responses is presented, where the fluid and the wing together are treated as a single dynamic system, and the equations of motion for the structure and flowfield are integrated simultaneously and interactively in the time domain.
Abstract: The present paper describes a numerical simulation of unsteady, subsonic aeroelastic responses. The technique accounts for aerodynamic nonlinearities associated with angles of attack, vortex-dominated flow, static deformations, and unsteady behavior. The fluid and the wing together are treated as a single dynamic system, and the equations of motion for the structure and flowfield are integrated simultaneously and interactively in the time domain. The method employs an iterative scheme based on a predictor-corrector technique. The aerodynamic loads are computed by the general unsteady vortex-lattice method and are determined simultaneously with the motion of the wing. Two models are used to demonstrate the technique: a rigid wing on an elastic support experiencing plunge and pitch about the elastic axis, and a continuous wing rigidly supported at the root chord experiencing spanwise bending and twisting. The time domain solution coupled with the unsteady vortex-lattice method provides the capability of graphically depicting wing and wake motion. Several graphs that illustrate the time domain behavior of the wing and wake are presented.

8 citations

Journal ArticleDOI
TL;DR: In this article, the effect of both geometric and aerodynamic twist on the induced drag of individual lifting surfaces in configuration flight including post-stall angles of attack has been investigated using a vortex lattice method.

8 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
20221
202133
202036
201947
201837
201731