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.
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TL;DR: In this paper, the influence of dihedral layout on lateral-directional dynamic stability of a tailless flying wing aircraft is discussed, where the dihedral angle along the spanwise sections is divided into three segments.
22 citations
13 Jun 2016
TL;DR: In this article, the authors presented an approach to correct three-dimensional VLM through coupling of two-dimensional transonic small disturbance (TSD) solutions along the span of an aircraft wing in order to accurately predict transonic aerodynamic loading and wave drag for transport aircraft.
Abstract: The need to rapidly scan large design spaces during conceptual design calls for computationally inexpensive tools such as the vortex lattice method (VLM). Although some VLM tools, such as Vorview have been extended to model fully-supersonic flow, VLM solutions are typically limited to inviscid, subcritical flow regimes. Many transport aircraft operate at transonic speeds, which limits the applicability of VLM for such applications. This paper presents a novel approach to correct three-dimensional VLM through coupling of two-dimensional transonic small disturbance (TSD) solutions along the span of an aircraft wing in order to accurately predict transonic aerodynamic loading and wave drag for transport aircraft. The approach is extended to predict flow separation and capture the attenuation of aerodynamic forces due to boundary layer viscosity by coupling the TSD solver with an integral boundary layer (IBL) model. The modeling framework is applied to the NASA General Transport Model (GTM) integrated with a novel control surface known as the Variable Camber Continuous Trailing Edge Flap (VCCTEF).
22 citations
TL;DR: The seminal aerodynamics literature provides analytic predictions of the loads due to sinusoidal gusts (Sears and von Karman, sharp-edged transverse gusts) and sinusoid motions (Theodorsen, Kussner, and others) as discussed by the authors.
Abstract: The seminal aerodynamics literature provides analytic predictions of the loads due to sinusoidal gusts (Sears and von Karman), sharp-edged transverse gusts (Kussner), sinusoidal motions (Theodorsen...
21 citations
TL;DR: In this article, an optimization technique was used to generate a wing-in-ground-effect (WIG) configuration which can achieve the maximum lift and satisfy the height stability criteria within the design constraints.
Abstract: An optimization technique was used to generate a wing-in-ground-effect (WIG) configuration which can achieve the maximum lift and satisfy the height stability criteria within the design constraints. For the analysis of the aerodynamic coefficients, the vortex lattice method (VLM) was applied with the inviscid and potential flow approximations. The sequential quadratic programming (SQP) method, which is a nonlinear optimization method, was employed as an optimization tool. The lift and moment coefficients, including the stability analysis computed by VLM, were compared with the experimental results of a medium-sized WIG, and a good correlation was found between them. In addition, the optimization tool was validated by finding the optimal position of the side wing attached on the WIG craft. Then, various optimum examples are shown, with generation of the wing section, the determination of the planform configuration, the aspect ratio, and the position of the tail wing within the design constraints. It was shown that the present optimization tool can be used effectively for the optimal design of a WIG craft.
21 citations
TL;DR: The proposed method can be used to solve the aeroelastic response problems of wings containing geometric nonlinearities and is suitable for predicting the nonlinear flutter speed and calculating the gust responses of a large-aspect-ratio wing in time domain.
21 citations