Extending the Leading-Edge Suction Analogy to Nonslender Delta Wings

Traub, Lance W.

doi:10.2514/1.c034939

Cited by 4 publications

(2 citation statements)

References 15 publications

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“…However, using the surface flow visualisation and the lift curve, we make an effort to explain the variation of the pitching moment coefficient. While doing so, we utilise the leading-edge suction analogy (Polhamus [51,52]; Traub [53]). The total lift of the flying wing can be considered as a summation of the potential lift that is generated due to the pressure distribution over the surface of the wing in the absence of the leading-edge vortex and the vortex-assisted lift, which is generated due to the leading-edge vortex assisted pressure distribution.…”

Section: Aerodynamic Characteristics and Surface Flow Featuresmentioning

confidence: 99%

An experimental investigation on the aerodynamic characteristics and vortex dynamics of a flying wing

Kumar,

Mandal,

Poddar

2024

Aeronaut. j.

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In this paper, we present a detailed experimental investigation mainly on the vortical flow fields and the associated vortex breakdown phenomena over a non-slender flying wing (sweep angle, ${\rm{\Lambda }}$ = 53°). In the process, the aerodynamic coefficients were also determined using a six-component force balance. Surface oil flow visualisation, surface pressure measurements and particle image velocimetry (PIV) measurements, in various crossflow planes and in a longitudinal plane passing through the leading-edge vortex core, were carried out at various Reynolds numbers to understand the flow field over the non-slender flying wing. Aerodynamic characteristics of the flying wing show local peaks and valleys in the pitching moment coefficient. The surface flow visualisation reveals that the nonlinearity of the pitching moment curve is due to the complex nature of vortical flow structures. The flow visualisation also demonstrates the presence of a wave-like surface pattern, and its size is found to reduce with increasing Reynolds numbers. The present PIV measurements confirm that this wave-like surface pattern is associated with vortex breakdown phenomena. These measurements also reveal that the vortex breakdown has not reached the apex of the wing, even at post-stall angle-of-attack. For pre-stall ( $\alpha $ = 20°) flow regimes, it is observed that the location of the vortex breakdown moves downstream as the Reynolds number increases, but this influence is minimised at near-stall ( $\alpha $ = 25°) and post-stall ( $\alpha $ = 30°) flow regimes. Reconstructed velocity field using the first 10 dominant proper orthogonal decomposition (POD) modes reveals that the nature of the vortex breakdown over the flying wing is a spiral-type vortex breakdown.

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Section: Aerodynamic Characteristics and Surface Flow Featuresmentioning

confidence: 99%

An experimental investigation on the aerodynamic characteristics and vortex dynamics of a flying wing

Kumar,

Mandal,

Poddar

2024

Aeronaut. j.

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“…Numerous comparisons validating this approach are present in the literature, especially with application to delta wings [3,[10][11][12][13][14][15]. Slender rectangular wings have also been modeled using the leading edge suction analogy; with terms associated with vortex lift caused by the leading edge and side edges [3,11].…”

Section: Introductionmentioning

confidence: 99%

Examination and Prediction of the Lift Components of Low Aspect Ratio Rectangular Flat Plate Wings

Traub

2023

Aerospace

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An investigation of the lift components present over low aspect ratio rectangular wings is presented. Wing aspect ratios ranging from 0.5 to 3 are examined using published experimental results and analytic analysis methods. The methods are based on the fundamental decomposition of Polhamus; that is, lift is attributed to a potential flow lift component coupled with a vortical lift component stemming from the leading and side edges of the flat plate wing. The analysis suggests a low sensitivity to Reynolds numbers spanning three orders of magnitude and brings into doubt the realization of a leading edge vortex lift component for wings with unswept leading edges under steady state conditions. The analytic prediction method of Purvis is shown to provide close accord with all experimental data sets when lift contributions caused by a leading edge vortex are excluded.

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Predicting the High-Angle-of-Attack Characteristics of a Delta Wing at Low Speed

Seraj

Martins

2022

Journal of Aircraft

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Extending the Leading-Edge Suction Analogy to Nonslender Delta Wings

Cited by 4 publications

References 15 publications

An experimental investigation on the aerodynamic characteristics and vortex dynamics of a flying wing

An experimental investigation on the aerodynamic characteristics and vortex dynamics of a flying wing

Examination and Prediction of the Lift Components of Low Aspect Ratio Rectangular Flat Plate Wings

Predicting the High-Angle-of-Attack Characteristics of a Delta Wing at Low Speed

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