A numerical solution for the minimum induced drag of nonplanar wings.

Lundry, J. L.; LlSSAMANf, P. B. S.

doi:10.2514/3.43901

Cited by 35 publications

(13 citation statements)

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“…Various analytic or low-order studies on minimizing induced drag using lifting-line theory and similar methods have been published since 1933. Whereas many of these studies approach the problem from a purely aerodynamic point of view [16][17][18][19][20][21][22][23][24], others follow an approach similar to that taken by Prandtl in 1933 [25][26][27][28][29][30][31][32][33][34][35][36][37][38]. Many of the early analytical studies in this second group consider the wing structure independent of the wing geometry.…”

Section:   Bmentioning

confidence: 99%

Minimum Induced Drag for Tapered Wings Including Structural Constraints

Taylor

Hunsaker

2020

Journal of Aircraft

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Section:   Bmentioning

confidence: 99%

Minimum Induced Drag for Tapered Wings Including Structural Constraints

Taylor

Hunsaker

2020

Journal of Aircraft

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“…The efficiency of vertical winglets has been estimated by Kuhlman et al [8] and Lundry et al [9], from analyses in the Trefftz plane. The efficiency factor k is defined as the ratio of induced drag coefficient for an elliptically loaded planar wing to the induced drag coefficient of the optimal nonplanar wing/winglet configuration having an equal projected span at equal lift coefficient.…”

Section: Wing and Wingletsmentioning

confidence: 99%

Analysis and Design of Wings and Wing/Winglet Combinations at Low Speeds

Chattot

2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

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Numerical treatment in Prandtl lifting-line theory of the nonlinearity associated with a 2-D lift curve, when the local incidence is larger than the incidence of maximum lift, is proposed. It is shown that the use of an artificial viscosity term makes the solution unique and allows the iterative method to converge to a physically meaningful solution, that is in agreement with the exact solution for the test case. The design and analysis of winglets is presented. The winglets considered are small fences placed upward at the tip of the wing to improve the wing efficiency by decreasing the induced drag. The effect of yaw on a wing equipped with such optimal winglets indicates that they provide weathercock stability.

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“…See for example Ref. 31 or the most common reference by Whitcomb (32) . Many designs have been carried out within the 'winglet' category.…”

Section: Far Field Drag Analysismentioning

confidence: 99%

“…The lifting line theory proposed by Prandtl (20,21) and extended to multiple surfaces by Munk (22) brought huge improvements in the lifting surface arrangements. Their theory has shown Promising mono-surface devices: swept wing tip/conventional winglet/shark winglet (28)(29)(30)(31)(32)(33)(34)(35)(36) .…”

Section: Jungle Of Existing Devicesmentioning

confidence: 99%

Downward pointing winglet design and assessment within the M-DAW research project

Hantrais-Gervois¹,

Grenon²,

Mann³

et al. 2009

Aeronaut. j.

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The design and performance analysis of a wing tip device proposed within the M-DAW project by ONERA is presented. A proto-design process is described and the device was thoroughly assessed (mainly with Reynolds-Averaged Navier-Stokes simulations). The process was further explained through wind-tunnel tests at both low speed and high speed in the pressurised and cryogenic European transonic wind tunnel in Cologne. The device is a downward pointing winglet designed for a retrofit scenario (the wing could be modified only within the 96% – 100% bounds of the span). It was designed to keep the wing root bending moment of the clean wing at cruise unchanged so that the aerodynamic gains are the net gains provided by the device that can be directly installed without structural modifications of the wing.

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A numerical solution for the minimum induced drag of nonplanar wings.

Cited by 35 publications

References 1 publication

Minimum Induced Drag for Tapered Wings Including Structural Constraints

Minimum Induced Drag for Tapered Wings Including Structural Constraints

Analysis and Design of Wings and Wing/Winglet Combinations at Low Speeds

Downward pointing winglet design and assessment within the M-DAW research project

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