Topic
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.
Papers published on a yearly basis
Papers
More filters
TL;DR: The UVLM simulation procedure is described and the first methodology to select properly the mesh and time-step sizes to achieve invariantUVLM simulation results under mesh refinement is described.
32 citations
TL;DR: In this article, an aeroservoelastic model was used to demonstrate the potential of active load alleviation using aerodynamic control surfaces using turbine rotors, where the structural model is a geometrically non-linear composite beam, which is linearized around equilibrium rotating conditions and coupled with time-domain aerodynamics given by a linearized 3D unsteady vortex lattice method.
Abstract: An aeroservoelastic model, capturing the structural response and the unsteady aerodynamics of turbine rotors, will be used to demonstrate the potential of active load alleviation using aerodynamic control surfaces. The structural model is a geometrically non-linear composite beam, which is linearized around equilibrium rotating conditions and coupled with time-domain aerodynamics given by a linearized 3D unsteady vortex lattice method. With much of the existing work relying on blade element momentum theory with various corrections, the use of the unsteady vortex lattice method in this paper seeks to complement and provide a direct higher fidelity solution for the unsteady rotor dynamics in attached flow conditions. The resulting aeroelastic model is in a state-space formulation suitable for control synthesis. Flaps are modeled directly in the vortex lattice description and using a reduced-order model of the coupled aeroelastic formulation, a linear-quadratic-Gaussian controller is synthesized and shown to reduce root mean square values of the root-bending moment and tip deflection in the presence of continuous turbulence. Similar trend is obtained when the controller is applied to the original non-linear model of the turbine. Trade-offs between reducing root-bending moment and suppressing the negative impacts on torsion due to flap deployment will also be investigated. Copyright © 2014 John Wiley & Sons, Ltd.
32 citations
TL;DR: In this article, a numerical method for the calculation of the nonlinear aerodynamic characteristics of wing-body configurations in steady low subsonic flow has been developed, based on a combination of the linear source-panel method for body and the non-linear vortex-lattice method for lifting surfaces and their separated wakes.
Abstract: A numerical method for the calculation of the nonlinear aerodynamic characteristics of wing-body configurations in steady low subsonic flow has been developed. The method is based on a combination of the linear source-panel method for the body and the nonlinear vortex-lattice method for the lifting surfaces and their separated wakes. Special emphasis is given to the understanding of the behavior and the computational accuracy of the numerical method. In order to demonstrate the capabilities of the present method, total and distributed loads are computed and compared with available experimental results. The computed examples cover simple configurations as well as more complicated geometries with greater relevance to modern missiles and aircraft. Details of the calculations clarify the significant nonlinear contribution of the body to the aerodynamic properties of the configuration. Good agreement was found between the computations and the experiments.
31 citations
31 citations