Full Article - Open Access.

Idioma principal


Souza, E. de; Silva, R. G. A. da; Cesnik, C. E. S.;

Full Article:

This paper presents studies about aerodynamic modeling for aeroelastic analyses of composite laminated flexible wings subjected to large displacements. An unsteady vortexlattice method (UVLM) is used, aiming reduction in computational costs when comparing with higher order CFD solutions. The UVLM has the advantage of being computationally simple, especially for complex configurations and for incompressible flow. Lifting surfaces subject to large angle of attack are very common in rotary wings area, but can also be important in the case of flapping wings in forward flight, where local fluid velocity components can lead to an effective angle of attack larger than the profile static stall limit. Since the vortex-lattice method is a potential method, without viscous effects, the boundary layer separation can not be captured. An engineering approach is then used to modify directly the pressure distribution based on an effective angle of attack calculated at each vortex-ring element. Applications to flat plate surfaces show good agreement with theory, and can predict hysteretic behavior in time response analyses. Application examples showing the ability to deal with multiple surfaces in rotary motion are also presented.

Full Article:

Palavras-chave: Unsteady Vortex-Lattice, stall model, large displacements, large rotations.,


DOI: 10.5151/meceng-wccm2012-18712

Referências bibliográficas
  • [1] Aono, H., Chimakurthi, S. K., Wu, P., Sällström, E., Stanford, B. K., Cesnik, C. E. S., Ifju, P., Ukeiley, L., and Shyy, W. (2010). A computational and experimental study of flexible flapping wing aerodynamics. In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4 - 7 January 2010, Orlando, Florida.
  • [2] Arnold, V. I. (1989). Mathematical Methods of Classical Mechanics. Graduate Texts in Mathematics. Springer-Verlag New York Inc.
  • [3] Banerjee, S. P. (2007). Aeroelastic Analysis of Membrane Wings. PhD thesis, Virginia Polythechnic Institute and State University, Blacksburg.
  • [4] Bierbooms,W. (1992). A comparison between unsteady aerodynamic models. Journal of Wind Engineering and Industrial Aerodynamics, 39(1-3):23–33.
  • [5] Chimakurthi, S. K., Stanford, B. K., Cesnik, C. E. S., and Shyy, W. (2009). Flapping wing cfd/csd aeroelastic formulation based on a co-rotational shell finite element. In 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 17th AIAA/ASME/AHS Adaptive Structures Conference 11th AIAA.
  • [6] Crisfield, M. A. (1990). A consistent co-rotational formulation for non-linear, threedimensional, beam-elements. Comput. Methods Appl. Mech. Eng., 81:131–150.
  • [7] de Souza, C. E., Silva, R. G. A., and Cesnik, C. E. S. (2012). Nonlinear aeroelastic framework based on vortex-lattice method and corotational shell finite element. In 53rd Structures, Structural Dynamics, and Materials Conference (SDM). AIAA.
  • [8] Fritz, T. E. and Long, L. N. (2004). Object-Oriented Unsteady Vortex Lattice Method for Flapping Flight. 41(6).
  • [9] Katz, J. (1981). Large-scale vortex-lattice model for the locally separated flow over wings. In AIAA 14th Fluid and Plasma Dynamics Conference.
  • [10] Katz, J. and Plotkin, A. (2001). Low Speed Aerodynamics. Cambridge University Press, Cambridge, UK, 2nd. edition.
  • [11] LAPACK (2012). Lapack linear algebra package - http://www.netlib.org/lapack/.
  • [12] Palacios, R., Murua, J., and Cook, R. (2010). Structural and aerodynamic models in nonlinear flight dynamics of very felixble aircraft. AIAA Journal, 48:2648–2659.
  • [13] Seber, G. and Bendiksen, O. O. (2008). Nonlinear flutter calculations using finite elements in a direct Eulerian-Lagrangian formulation. AIAA Journal, 46(6):1331–1341.
  • [14] Shabana, A. A. (2005). Dynamics of Multibody Systems. Cambridge University Press, third edition edition.
  • [15] Stanford, B. and Beran, P. (2009). An updated lagrangian shell and vortex lattice aeroelastic framework for flapping wings. In IFASD 2009.
  • [16] Stanford, B. K. and Beran, P. S. (2010). Analytical Sensitivity Analysis of an Unsteady Vortex-Lattice Method for Flapping-Wing Optimization. Journal of Aircraft, 47(2):647– 662.
  • [17] Su, W. and Cesnik, C. E. S. (2010). Nonlinear aeroelastic simulations of a flapping wing micro air vehicle using two unsteady aerodynamic formulations. In 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, number AIAA-2010-2887, pages 1–22.
  • [18] Theodorsen, T. (1935). General theory of aerodynamic instability and the mechanism of flutter. Technical Report NACA-TR-496, NACA.
  • [19] Wang, Z. (2004). Time-Domain Simulations of Aerodynamic Forces on Three- Dimensional Configurations, Unstable Aeroelastic Responses, and Control by Neural Network Systems. PhD thesis, Virginia Polytechnic Institute and State University
Como citar:

Souza, E. de; Silva, R. G. A. da; Cesnik, C. E. S.; "AN OBJECT-ORIENTED UNSTEADY VORTEX LATTICE METHOD FOR AEROELASTIC ANALYSES OF HIGHLY FLEXIBLE WINGS.", p. 2064-2083 . In: In Proceedings of the 10th World Congress on Computational Mechanics [= Blucher Mechanical Engineering Proceedings, v. 1, n. 1]. São Paulo: Blucher, 2014.
ISSN 2358-0828, DOI 10.5151/meceng-wccm2012-18712

últimos 30 dias | último ano | desde a publicação