Inclusion of Aeroelastic Twist into the CFD Analysis of the Twin-Engine NASA Common Research Model

Benedict, Kent A.; Hedges, Linda; Robinson, A. A.; Peddiraju, Pravin; Papadopoulos, Arthur; Skaperdas, Vangelis; Tinoco, Edward N.; Eberhardt, Scott

doi:10.2514/6.2014-0251

Cited by 8 publications

(1 citation statement)

References 11 publications

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“…It has been demonstrated that the lift and drag of rigid and flexible wings in free-stream may differ by up to 6% due to wing twist, 1,2 where the twist is a function of the torsional rigidity. This indicates that the wing torsional rigidity can be tailored to produce desired aerodynamic characteristics at different operating conditions.…”

Section: Introductionmentioning

confidence: 99%

The effect of static deformation on the lift loss phenomenon of an ABS downforce producing wing in ground effect

Aquino

Diasinos

2021

Proceedings of the Institution of Mechanical Engineers, Part D:

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The proximity of a downforce producing wing to the ground has a significant effect on the generation of aerodynamic loads and flow structures. However, a rigid body assumption for the wing may lead to inaccuracies in the estimation of these loads. Static loosely-coupled Fluid-Structure Interaction (FSI) simulations were performed at Reynolds numbers of 4.64·105 and 6.96·105 and ground clearances ranging from 0.053 c to 0.223 c to investigate the effect of deformation in an ABS wing. Results of these simulations demonstrated that wing deflection increased the height at which lift loss occurred, as the reduced wing tip ground clearance led to an earlier main wing vortex breakdown and greater boundary layer separation. The increase in Reynolds number for a constant chord length induced larger variations in critical height: the critical height increased by 0.011 c at Re = 4.64·105 and by 0.021 c at Re = 6.96·105. The larger variation in critical height at the high Reynolds number cases was due to the increase in the magnitude of the aerodynamic loads, and larger deflections.

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Section: Introductionmentioning

confidence: 99%

The effect of static deformation on the lift loss phenomenon of an ABS downforce producing wing in ground effect

Aquino

Diasinos

2021

Proceedings of the Institution of Mechanical Engineers, Part D:

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Using wing model deformation for improvement of CFD results of ESWIRP project

Vrchota

Prachař

2018

CEAS Aeronaut J

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Static loads evaluation in a flexible aircraft using high-fidelity fluid–structure iteration tool (E2-FSI): extended version

Verri

Bussamra

Morais

et al. 2020

J Braz. Soc. Mech. Sci. Eng.

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This paper presents a fluid-structure iteration method applied as a study case to a conventional transport aircraft with wing aspect ratio of 12. It evaluates the nonlinear structure effect on the calculation of static limit loads. The numerical tool presented herein is named E2-FSI, which stands for nonlinear high-fidelity static fluid-structure iteration, developed for high flexibility static aeroelastic evaluations. A discussion about the use and the applicability of high-fidelity static fluid-structure iteration for the calculation of static loads is presented as part of the conclusion, for both current and future conventional transport aircraft.

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Inclusion of Aeroelastic Twist into the CFD Analysis of the Twin-Engine NASA Common Research Model

Cited by 8 publications

References 11 publications

The effect of static deformation on the lift loss phenomenon of an ABS downforce producing wing in ground effect

The effect of static deformation on the lift loss phenomenon of an ABS downforce producing wing in ground effect

Using wing model deformation for improvement of CFD results of ESWIRP project

Static loads evaluation in a flexible aircraft using high-fidelity fluid–structure iteration tool (E2-FSI): extended version

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