Low-Order Method for Prediction of Separation and Stall on Unswept Wings

Hosangadi, Pranav; Gopalarathnam, Ashok

doi:10.2514/1.c036027

Cited by 4 publications

(2 citation statements)

References 63 publications

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“…More recently, modified VLMs and LLTs have been introduced to extend to unsteady-flow problems the operating conditions reliably simulated by the solvers (see, for instance, [9][10][11][12][13][14][15]). In particular, Drela [16] and Katz and Plotkin [8] presented an approximate unsteady version of the Kutta-Joukowski theorem that has been extensively used in unsteady-flow applications of VLMs and LLTs (see, for instance, [17][18][19][20][21][22][23][24][25][26] for VLM applications and [27][28][29][30][31][32] for LLT applications).…”

Section: Introductionmentioning

confidence: 99%

Kutta–Joukowski Theorem for Unsteady Linear Aerodynamics

Gennaretti

Giansante

2022

AIAA Journal

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This paper presents the extension of the Kutta-Joukowski theorem to unsteady linear aerodynamics. Starting from the formulation developed by Theodorsen for the solution of the velocity potential for circulatory flows around thin, rectilinear airfoils, the frequency response function between bound circulation and circulatory lift is derived. To provide a formulation suitable for time-domain applications, two finite-state approximations of the Kutta-Joukowski frequency response function, with different degrees of complexity and accuracy, are also proposed. The validity of the derived unsteady Kutta-Joukowski theorem is verified by correlation with numerical predictions of the circulatory lift given by a validated boundary-elementmethod solver for potential flows. Furthermore, the proposed finite-state approximations of the unsteady Kutta-Joukowski theorem are applied to problems concerning the circulatory lift response to damped oscillatory airfoil motion and gust perturbation. The higher-accuracy finite-state model provides predictions that correspond perfectly to those obtained by the con-

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Section: Introductionmentioning

confidence: 99%

Kutta–Joukowski Theorem for Unsteady Linear Aerodynamics

Gennaretti

Giansante

2022

AIAA Journal

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“…The vortex lattice method (VLM) is a commonly used panel method for aerodynamic analysis of lifting bodies [17]. The VLM is widely used in aircraft wing design and optimization in subsonic flights [18], aerodynamic prediction at near-stall and post-stall flight conditions [19], morphing wing-tip aerodynamic analysis [20], etc. With a no-sideslip assumption, additional aerodynamic effects induced by wind shear were computed and added to the quasi-static aerodynamic model.…”

Section: Introductionmentioning

confidence: 99%

The Optimization of Aircraft Acceleration Response and EDR Estimation Based on Linear Turbulence Field Approximation

Wang

Gao

et al. 2021

Atmosphere

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The estimation of aircraft vertical acceleration response to atmospheric turbulence is fundamental to acceleration-based eddy dissipation rate (EDR) estimation. The linear turbulence field approximation with the wind gradients effects is utilized to describe the turbulence effects on civil aviation aircraft. To consider the wind gradients effects, the aircraft was modeled by a cruciform assembly in this study. A vertical acceleration estimation based on the unsteady vortex lattice method (UVLM) was proposed, in which the air-compression effects in high-subsonic flight were compensated by the Karman–Tsien rule. Results indicate that compared with the wing-tail assembly, the cruciform assembly with the wind gradients effects has better accuracy in computing acceleration response. The vertical acceleration response only induced by turbulence can be obtained for acceleration-based EDR estimation. Furthermore, with the optimized acceleration response, the estimated EDR value has got better accuracy and stability.

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