Aerodynamics of high-lift, low-aspect-ratio unswept wings

Katz, Joseph

doi:10.2514/3.10231

Cited by 12 publications

(8 citation statements)

References 2 publications

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“…Comparing the results of various NACA 4412 wings with the same configuration, it can be seen that as the aspect ratio increases, the pressure distribution over the surface of the multi-flap system converge towards the results obtained for a NACA 4412 wing. For lower aspect ratio wings, the span-wise vorticity gradients are stronger and thus influence the pressure distribution over the surface of the wing significantly [9]. The ability of the multi-flap system to withstand powerful gusting flows is the most important aspect of its functionality.…”

Section: Panel Methods Results For Bio-inspired Multi-flap Systemmentioning

confidence: 99%

“…One of the most significant contributions of this technology is in the development of viscous-inviscid panel method solvers for high speed aerodynamic analysis of complex wing geometries for preliminary design stages [6][7][8][9]. These methods offer faster assessment of flow variables over the surface of the wing in comparison to traditional Computational Fluid Dynamic (CFD) solvers and thus can be used for initial analysis of a multi-flap wing.…”

Section: Introductionmentioning

confidence: 99%

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A three dimensional unsteady iterative panel method with vortex particle wakes and boundary layer model for bio-inspired multi-body wings

2015

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The ability of UAVs to operate in complex and hostile environments makes them useful in military and civil operations concerning surveillance and reconnaissance. However, limitations in size of UAVs and communication delays prohibit their operation close to the ground and in cluttered environments, which increase risks associated with turbulence and wind gusts that cause trajectory deviations and potential loss of the vehicle. In the last decade, scientists and engineers have turned towards bio-inspiration to solve these issues by developing innovative flow control methods that offer better stability, controllability, and maneuverability. This paper presents an aerodynamic load solver for bio-inspired wings that consist of an array of feather-like flaps installed across the upper and lower surfaces in both the chord-and spanwise directions, mimicking the feathers of an avian wing. Each flap has the ability to rotate into both the wing body and the inbound airflow, generating complex flap configurations unobtainable by traditional wings that offer improved aerodynamic stability against gusting flows and turbulence. The solver discussed is an unsteady three-dimensional iterative doublet panel method with vortex particle wakes. This panel method models the wake-body interactions between multiple flaps effectively without the need to define specific wake geometries, thereby eliminating the need to manually model the wake for each configuration. To incorporate viscous flow characteristics, an iterative boundary layer theory is employed, modeling laminar, transitional and turbulent regions over the wing's surfaces, in addition to flow separation and reattachment locations. This technique enables the boundary layer to influence the wake strength and geometry both within the wing and aft of the trailing edge. The results obtained from this solver are validated using experimental data from a low-speed suction wind tunnel operating at Reynolds Number 300,000. This method enables fast and accurate assessment of aerodynamic loads for initial design of complex wing configurations compared to other methods available.

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Section: Panel Methods Results For Bio-inspired Multi-flap Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A three dimensional unsteady iterative panel method with vortex particle wakes and boundary layer model for bio-inspired multi-body wings

2015

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“…According to Katz (1989) low aspect ratio wings have to be designed using a three-dimensional model. Thus a 3D aeroelastic analysis model is developed to investigate the possible drag reduction achievable on an F1 rear wing.…”

Section: Three Dimensional Modelmentioning

confidence: 99%

“…4. By using a multi-element airfoil, the angle-of-attack of the rearward element can be increased, thereby increasing the overall downforce created by the assembly (Katz 1989). In the present study, the rear element is not considered to simplify the model.…”

Section: Model Geometrymentioning

confidence: 99%

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Aeroelastic tailoring using lamination parameters

Thuwis

Breuker

Abdalla

et al. 2009

Struct Multidisc Optim

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The aim of the present work is to passively reduce the induced drag of the rear wing of a Formula One car at high velocity through aeroelastic tailoring. The angle-ofattack of the rear wing is fixed and is determined by the required downforce needed to get around a turn. As a result, at higher velocity, the amount of downforce and related induced drag increases. The maximum speed on a straight part is thus reduced due to the increase in induced drag. A fibre reinforced composite torsion box with extension-shear coupled upper and lower skins is used leading to bendingtorsion coupling. Three-dimensional static aeroelastic analysis is performed loosely coupling the Finite Element code Nastran and the Computational Fluid Dynamics panel code VSAERO using ModelCenter. A wing representative of Formula One rear wings is optimised for minimum induced drag using a response surface methodology. Results indicate that a substantial induced drag reduction is achievable while maintaining the desired downforce during low speed turns.

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Application Of Aeronautical Engineering Techniques To The Design Of Control Surfaces For Human Powered Submarines

Drinkard

Proceedings OCEANS

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Aerodynamics of high-lift, low-aspect-ratio unswept wings

Cited by 12 publications

References 2 publications

A three dimensional unsteady iterative panel method with vortex particle wakes and boundary layer model for bio-inspired multi-body wings

A three dimensional unsteady iterative panel method with vortex particle wakes and boundary layer model for bio-inspired multi-body wings

Aeroelastic tailoring using lamination parameters

Application Of Aeronautical Engineering Techniques To The Design Of Control Surfaces For Human Powered Submarines

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