Lift Prediction of Spanwise Cambered Delta Wings

Traub, Lance W.

doi:10.2514/2.2486

Cited by 9 publications

(1 citation statement)

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“…However, the VLM, with various modifications and enhancements, is used even today for low-order modeling and engineering applications, with recent examples ranging from flight dynamics analysis [9,10], analysis of yacht sails [11], calculation of aerodynamic interference effects [12][13][14], post-stall analysis [15,16], flapping-wing analysis [17][18][19][20], wind turbines [21,22], design optimization [19,23,24] and aeroelasticity [25][26][27]. Modified VLMs have also been extensively used for modeling steady and unsteady flows past delta-wings [28], propeller aerodynamics [29], propeller-wing interactions [30], ground effect and formation flight [31][32][33][34], compressibility effects and transonic flow over wings [35,36], system identification [37], and for rapid performance prediction in adaptive control of aircraft [38,39]. The current work, along similar lines, aims to extend the VLM for modeling separation and stall.…”

Section: Introductionmentioning

confidence: 99%

A Low-Order Method for Prediction of Separation and Stall on Unswept Wings

Hosangadi¹,

Gopalarathnam²

2020

Preprint

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A low-order method is presented for aerodynamic prediction of wings operating at nearstall and post-stall flight conditions. The method is intended for use in design, modeling, and simulation. In this method, the flow separation due to stall is modeled in a vortex-lattice framework as an effective reduction in the camber, or "decambering." For each section of the wing, a parabolic decambering flap, hinged at the separation location of the section, is calculated through iteration to ensure that the lift and moment coefficients of the section match with the values from the two-dimensional viscous input curves for the effective angle of attack of the section. As an improvement from earlier low-order methods, this method also predicts the separation pattern on the wing. Results from the method, presented for unswept wings having various airfoils, aspect ratios, taper ratios, and small, quasi-steady roll rates, are shown to agree well with experimental results in the literature, and computational solutions obtained as part of the current work.

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