Physical properties of Maskell's induced drag integral

Kusunose, Kazuhiro; Crowder, J. P.

doi:10.2514/6.2001-421

Cited by 13 publications

(6 citation statements)

References 9 publications

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“…8 shows that the induced drag can be significantly reduced for low altitude when cant angle reaches values between δ = [−60 • , −30 • ]. It can be shown that external lift distribution with smooth variation better performs regarding induced drag [22]. Observing Fig.…”

Section: B Sensitivity To Flight Conditionsmentioning

confidence: 78%

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Parametric Analysis of an Active Winglet Concept for High Aspect Ratio Wing Using CFD/CSM Computations

Delavenne

Barriety

Vetrano

et al. 2020

Aiaa Aviation 2020 Forum

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This paper presents a parametric analysis of an active winglet concept applied to a high aspect ratio wing. The technology studied here only consists in a single degree of freedom wing-tip whose only the cant angle deflection can be controlled. The main parameters under study are the hinge line location and its orientation with respect to the longitudinal axis of the aircraft. High-fidelity aerodynamic and structural computations are used to assess the impact of the device on both drag and loads. The influence of cant angle deflections on flutter characteristics is also evaluated. First a "wing only" configuration is studied and the results are compared with complete aircraft computations to take into account the contributions due to the trim. It is shown that the hinge line parameters highly influence the drag evolution with cant angle but with limited impact on the minimum area -in which we are interested in. Loads are significantly impacted by both cant variations and hinge line geometry. Regarding dynamic characteristics, the mode sequence is dependent on the cant deflection and massively impacts flutter onset.

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Section: B Sensitivity To Flight Conditionsmentioning

confidence: 78%

“…One can observed that the lift is shifted more inward for the innermost hinge and that the lift variation close to the tip are stronger. As emphasized in [22] the induced drag evolves as the lift times its first derivative with respect to span which explains the strongest increase of drag for the large winglet.…”

Section: A Impact Of Hinge Line Locationmentioning

confidence: 90%

Parametric Analysis of an Active Winglet Concept for High Aspect Ratio Wing Using CFD/CSM Computations

Delavenne

Barriety

Vetrano

et al. 2020

Aiaa Aviation 2020 Forum

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“…Maskell's formula only by a compressibility correction F ∇ρ which involves density gradients and variations. As S e extends further away from the body surface, this correction gradually vanishes while F KJ and F MSK respectively reduce to the incompressible Kutta-Joukowski theorem (see [5]) and the incompressible Maskell's formula (see [16][17][18][19]59]).…”

Section: Development Of An Invariant Formulation Embedding Classical ...mentioning

confidence: 99%

Invariant Vortex-Force Theory Extending Classical Aerodynamic Theories to Transonic Flows

2022

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“…In the end it was shown that, in transonic flows, F ρl + F trans m ρ differs from the classical Kutta-Joukowski theorem and Maskell's formula only by a compressibility correction F ∇ρ which involves density gradients and variations. As S e extends further away from the body surface, this correction gradually vanishes while F KJ and F MSK respectively reduce to the incompressible Kutta-Joukowski theorem (see [5]) and the incompressible Maskell's formula (see [16][17][18][19]59]). As it happens, it was shown by several authors that the incompressible Kutta-Joukowski theorem can predict the lift in compressible flows [8,9,43].…”

Section: A Links With the Kutta-joukowski Lift Theorem And Maskell's ...mentioning

confidence: 99%

An invariant vortex-force theory related to classical far-field analyses in transonic flows

Fournis¹,

Bailly²,

Tognaccini

2021

Aiaa Aviation 2021 Forum

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Recent studies about the Lamb vector have led to the development of the vortex-force theory, a formulation able to predict the aerodynamic force in compressible flows and decompose it into lift, lift-induced drag and profile drag. Here, a revised formulation of the vortex-force theory developed at ONERA in collaboration with the University of Naples is presented and applied to steady transonic flows. In the mathematical developments, special care is given to the presence of shock wave discontinuities within the flow field. The equivalence between the new definition, the Kutta-Joukowski lift theorem, Maskell's lift-induced drag formula and Betz's profile drag formula is emphasized. The revised formulation also presents several practical advantages: the decomposition is naturally independent of the reference point chosen for the calculation of moment transformations, and the computation can be performed in a better refined part of the grid. The formulation is finally tested on the NASA Common Research Model (CRM) wing-fuselage configuration in cruise flight conditions.

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Physical properties of Maskell's induced drag integral

Cited by 13 publications

References 9 publications

Parametric Analysis of an Active Winglet Concept for High Aspect Ratio Wing Using CFD/CSM Computations

Parametric Analysis of an Active Winglet Concept for High Aspect Ratio Wing Using CFD/CSM Computations

Invariant Vortex-Force Theory Extending Classical Aerodynamic Theories to Transonic Flows

An invariant vortex-force theory related to classical far-field analyses in transonic flows

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