Proceedings ArticleDOI
Convergence characteristics of nonlinear vortex-lattice methods for configuration aerodynamics
TLDR
In this paper, the convergence characteristics of an iterative, nonlinear vortex-lattice method are investigated, and the initial conditions for the first iteration on the computed aerodynamic coefficients and on the flow-field details are presented.Abstract:
Nonlinear panel methods have no proof for the existence and uniqueness of their solutions. The convergence characteristics of an iterative, nonlinear vortex-lattice method are, therefore, carefully investigated. The effects of several parameters, including (1) the surface-paneling method, (2) an integration method of the trajectories of the wake vortices, (3) vortex-grid refinement, and (4) the initial conditions for the first iteration on the computed aerodynamic coefficients and on the flow-field details are presented. The convergence of the iterative-solution procedure is usually rapid. The solution converges with grid refinement to a constant value, but the final value is not unique and varies with the wing surface-paneling and wake-discretization methods within some range in the vicinity of the experimental result.read more
Citations
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Journal ArticleDOI
Convergence characteristics of a vortex-lattice method for nonlinear configuration aerodynamics
TL;DR: In this paper, the convergence characteristics of a vortex-lattice method for the high-angle-of-attack, nonlinear aerodynamics of aircraft and missile configurations are studied parametrically.
Dissertation
Numerical Wing/Store Interaction Analysis of a Parametric F16 Wing
TL;DR: Inman et al. as mentioned in this paper developed a new numerical methodology to examine fluid-structure interaction of a wing/pylon/store system, which is based on an F16 configuration that was identified to induce flutter in flight at subsonic speeds.
Desarrollo de una Plataforma de Co-Simulación para el Estudio Integral de Turbinas Eólicas: Aspectos Teóricos y de Modelado
TL;DR: In this paper, el sistema dinamico bajo estudio is particionado en tres subsistemas: i) un modelo multicuerpo rigido for the estructura de la turbina; ii) unmodelo aerodinamico basado en el metodo de red de vortices no lineal e inestacionario (Unsteady Vortex-Lattice Method, UVLM) for estimar las cargas sobre las palas of the turbina, and iii) a maqu
Proceedings ArticleDOI
Lift due to thickness for low aspect ratio wings in incompressible flow
S. S. Dodbele,Allen Plotkin +1 more
TL;DR: In this paper, the effects of thickness on lift for low aspect ratio wings in steady incompressible inviscid flow at moderate angles of attack were investigated. But the results were limited to a single wing.
References
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Journal ArticleDOI
Calculation of potential flow about arbitrary bodies
J.L. Hess,A.M.O. Smith +1 more
Vortex-lattice FORTRAN program for estimating subsonic aerodynamic characteristics of complex planforms
J. E. Lamar,R. J. Margason +1 more
TL;DR: Computer program for estimating subsonic aerodynamic characteristics of various aerodynamic configurations is presented and examples and typical running times of various types of configurations are provided.
Theoretical symmetric span loading at subsonic speeds for wings having arbitrary plan form
John Deyoung,Charles W Harper +1 more
TL;DR: In this paper, a method for finding the symmetric span loading for a certain class of wings can be found, where the geometry of these wings is limited only to the extent that they must have symmetry about the root chord, must have a straight quarter-chord line over the semispan, and must have no discontinuities in twist.
Journal ArticleDOI
Nonlinear prediction of the aerodynamic loads on lifting surfaces
TL;DR: In this paper, a numerical procedure was used to predict the nonlinear aerodynamic characteristics of lifting surfaces of low aspect ratio at high angles of attack for low subsonic Mach numbers.
The Calculation of Aerodynamic Loading on Surfaces of Any Shape
TL;DR: In this article, the authors present a method for calculating aerodynamic loads on wings of arbitrary shape based on potential theory and use a general mathematical formula for continuous loading on a wing which is equivalent to a double Fourier series with unknown coefficients.