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Thomas Lambert
University of Liège

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Proceedings article
Published: 06 January 2019 in AIAA Scitech 2019 Forum
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ACS Style

Thomas Lambert; Nicolas Warbecq; Patrick Hendrick; Robert Nudds; Thomas Andrianne; Grigorios Dimitriadis. Numerical and Experimental Investigation of Tandem Wing Flyers. AIAA Scitech 2019 Forum 2019, 1 .

AMA Style

Thomas Lambert, Nicolas Warbecq, Patrick Hendrick, Robert Nudds, Thomas Andrianne, Grigorios Dimitriadis. Numerical and Experimental Investigation of Tandem Wing Flyers. AIAA Scitech 2019 Forum. 2019; ():1.

Chicago/Turabian Style

Thomas Lambert; Nicolas Warbecq; Patrick Hendrick; Robert Nudds; Thomas Andrianne; Grigorios Dimitriadis. 2019. "Numerical and Experimental Investigation of Tandem Wing Flyers." AIAA Scitech 2019 Forum , no. : 1.

Journal article
Published: 18 April 2017 in Aerospace
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Flapping flight is an increasingly popular area of research, with applications to micro-unmanned air vehicles and animal flight biomechanics. Fast, but accurate methods for predicting the aerodynamic loads acting on flapping wings are of interest for designing such aircraft and optimizing thrust production. In this work, the unsteady vortex lattice method is used in conjunction with three load estimation techniques in order to predict the aerodynamic lift and drag time histories produced by flapping rectangular wings. The load estimation approaches are the Katz, Joukowski and simplified Leishman–Beddoes techniques. The simulations’ predictions are compared to experimental measurements from wind tunnel tests of a flapping and pitching wing. Three types of kinematics are investigated, pitch-leading, pure flapping and pitch lagging. It is found that pitch-leading tests can be simulated quite accurately using either the Katz or Joukowski approaches as no measurable flow separation occurs. For the pure flapping tests, the Katz and Joukowski techniques are accurate as long as the static pitch angle is greater than zero. For zero or negative static pitch angles, these methods underestimate the amplitude of the drag. The Leishman–Beddoes approach yields better drag amplitudes, but can introduce a constant negative drag offset. Finally, for the pitch-lagging tests the Leishman–Beddoes technique is again more representative of the experimental results, as long as flow separation is not too extensive. Considering the complexity of the phenomena involved, in the vast majority of cases, the lift time history is predicted with reasonable accuracy. The drag (or thrust) time history is more challenging.

ACS Style

Thomas Lambert; Norizham Abdul Razak; Grigorios Dimitriadis. Vortex Lattice Simulations of Attached and Separated Flows around Flapping Wings. Aerospace 2017, 4, 22 .

AMA Style

Thomas Lambert, Norizham Abdul Razak, Grigorios Dimitriadis. Vortex Lattice Simulations of Attached and Separated Flows around Flapping Wings. Aerospace. 2017; 4 (2):22.

Chicago/Turabian Style

Thomas Lambert; Norizham Abdul Razak; Grigorios Dimitriadis. 2017. "Vortex Lattice Simulations of Attached and Separated Flows around Flapping Wings." Aerospace 4, no. 2: 22.

Brief report
Published: 01 February 2017 in AIAA Journal
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The Unsteady Vortex Lattice Method (UVLM) is an approach widely used to estimate the aerodynamic loads in unsteady subsonic flows. It is based on modeling the camber surface of a lifting body by means of bound vortex rings. Even though this method has been known and used for several decades, there is little discussion of the modeling of the leading-edge suction in the literature. To address this concern, Simpson et al. [1] presented a comparison of two different ways to model this effect for the case of uncambered airfoils and wings in harmonic pitch or plunge motions. They concluded that the Joukowski method converges significantly faster than the Katz technique as the number of chorwise panels is increased. The present paper is an extension of the study by Simpson et al. to cambered lifting surfaces. It shows that the presence of camber can change radically the convergence performance of the two methods. For cambered wings, the Katz approach converges significantly faster than the Joukowski technique.Peer reviewe

ACS Style

Thomas Lambert; Grigorios Dimitriadis. Induced Drag Calculations with the Unsteady Vortex Lattice Method for Cambered Wings. AIAA Journal 2017, 55, 668 -672.

AMA Style

Thomas Lambert, Grigorios Dimitriadis. Induced Drag Calculations with the Unsteady Vortex Lattice Method for Cambered Wings. AIAA Journal. 2017; 55 (2):668-672.

Chicago/Turabian Style

Thomas Lambert; Grigorios Dimitriadis. 2017. "Induced Drag Calculations with the Unsteady Vortex Lattice Method for Cambered Wings." AIAA Journal 55, no. 2: 668-672.