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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 article, the authors performed numerical simulations for uniform, yawed, wind shear flow conditions, and various tower cases using the nonlinear vortex correction method with time-marching free wake.
Abstract: The blade-tower interaction of upwind horizontal axis wind turbines has become important to aerodynamic loading as the systems become larger. However, there are not enough studies describing these phenomena. To investigate this interaction, we performed numerical simulations for uniform, yawed, wind shear flow conditions, and various tower cases using the nonlinear vortex correction method with time-marching free wake. At 5 m/s, the change in the normal force coefficient is approximately 10% of the average. The blade root region has a larger azimuth range of the interaction and a bigger change in aerodynamic loading. The blade-tower interaction decreases as the yaw error and wind shear exponent increases. The interaction due to tower radius variations is higher than that due to tower clearance variations. With regard to stochastic load, the blade-tower interaction may affect the total fatigue load at low wind speed and in a more unstable atmospheric condition.

25 citations

Proceedings ArticleDOI
13 Jan 2014
TL;DR: A summary of the computational aerodynamic performance tools and analyses for the development of the Surfing Aircraft Vortices for Energy (SAVE) formation flight concept is presented in this article.
Abstract: A summary of the computational aerodynamic performance tools and analyses for the development of the Surfing Aircraft Vortices for Energy (SAVE) formation flight concept is presented. Aerodynamic analysis is accomplished using several, multi-fidelity prediction methods, including a vortex lattice method (VLM) approach, a panel method to model body effects, and a high-fidelity hybrid computational fluid dynamics (CFD) method that couples a Reynolds Averaged Navier-Stokes (RANS) flow solver for the near-body simulation with a quasi-3D RANS approach for the evolution of wakes over long longitudinal distances. Computational analysis is used to develop a comprehensive aerodynamic database for flight simulation and control law design, to develop a drag benefit “map”, which is used to determine the optimum location of the trailing airplane relative to the leading airplane wake, and to compare with flight-derived performance data to validate the use of CFD for the SAVE program. Finally, an extension of the hybrid CFD method and initial results for a 3-airplane echelon formation to highlight the multiple wake interaction effects and complex flow physics is presented.

25 citations

Journal ArticleDOI
TL;DR: In this paper, the problem of modeling steady and unsteady aerodynamic interference is discussed, and the general unstaidy vortex-lattice method is used to model the flowfield.
Abstract: The problem of modeling steady and unsteady aerodynamic interference is discussed. A configuration resembling the X-29 is used as an example. The general unsteady vortex-lattice method is used to model the flowfield. By considering the components operating alone and as members of the complete configuration, we demonstrate the importance of accurately simulating the wakes of the upstream components. The wakes of the canards as well as the canards themselves have a strong negative influence on the lift generated by the main wing; the main wing has a positive influence on the lift generated by the canards. The forward sweep of the main wing tends to focus the generated upwash in the vicinity of the canards. It is shown that the maximum influence of the vorticity shed from the canards does not develop until the shed vorticity convects downstream directly over the main wing. The general unsteady vortex-lattice method appears to be a reasonably accurate model of closely coupled, vorticity-dominated flowfields as long as the lines of the separation are known and vortex bursting does not occur near the wings.

25 citations

Journal ArticleDOI
TL;DR: In this paper, a method for calculating the longitudinal aerodynamic coefficients and the pressure distributions on a body at reasonably high angles of attack is presented, where the body is represented by a combination of source elements and vortex-lattice elements.
Abstract: A method for calculating the longitudinal aerodynamic coefficients and the pressure distributions on a body at reasonably high angles of attack is presented. The body is represented by a combination of source elements and vortex-lattice elements, including separation of the vortices at increasing angles of attack. The method is self-consistent in that the body and the separated vortex wake are treated as an integrated interacting system. The location of the separation line can be included as an arbitrary input from experimental data or can be evaluated approximately by a pressure-dependent criterion. Calculated values of the aerodynamic coefficients and pressure distributions on cone-cylinder and ogive-cylinder bodies compare well, qualitatively and quantitatively, with experimental data, including simulation of the dependence on Reynolds number.

25 citations


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