Multi-fidelity Fluid-Structure Interaction Analysis of a Membrane Wing
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Multi-fidelity Fluid-Structure Interaction Analysis of a Membrane Wing

Authors: M. Saeedi, R. Wuchner, K.-U. Bletzinger

Abstract:

In order to study the aerodynamic performance of a semi-flexible membrane wing, Fluid-Structure Interaction simulations have been performed. The fluid problem has been modeled using two different approaches which are the vortex panel method and the numerical solution of the Navier-Stokes equations. Nonlinear analysis of the structural problem is performed using the Finite Element Method. Comparison between the two fluid solvers has been made. Aerodynamic performance of the wing is discussed regarding its lift and drag coefficients and they are compared with those of the equivalent rigid wing.

Keywords: CFD, FSI, Membrane wing, Vortex panel method.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1099593

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[1] Blondeau, J., Richeson, J., and Pines, J.D.: Desing, development and testing of a morphing aspect ratio wing using an inflatable telescopic spar. AIAA Paper 2003-1718, April 2003.
[2] Bowmann, J., Sanders, B., Cannon, B., Kudva, J, Joshi, S., Weisshaar, T.: Development of Next Generation Morphing Aircraft Structures. AIAA 2007-1730, April 2007.
[3] Barbarino, S., Dettmer W., Friswell M.: Morphing Trailing Edges with Shape Memory Alloy Rods, ICAST 2010
[4] Lian Y., Shyy W., Numerical Simulation of Membrane Wing Aerodynamics for Micro Air Vehicle Applications, AIAA J. of Aircraft, Vol. 42, No. 4, July.-Aug 2005
[5] Abdulrahim, M., Garcia, H., and Lind, R.: Flight Characteristics of Shaping the Membrane Wing of a Micro Air Vehicle, AIAA J. of Aircraft, Vol. 42, No. 1, Jan.-Febr. 2005
[6] Valasek, J.: Morphing Aerospace Vehicles and Structures. John Wiley, 2.
[7] Levin, O., Shyy, W.: Optimization of a flexible low Reynolds number airfoil. AIAA Paper 2001-16055, Jan. 2001.
[8] Waszak, R.M., Jenkins, N.L., Ifju P., Stability and Control Properties of an Aeroelastic Fixed Wing Micro Aerial Vehicle, AIAA Paper 2001-4005, 2001.
[9] R. Ormiston. Theoretical and Experimental Aerodynamics of the Sailwing, J. Aircraft, 1971
[10] Patankar S.V., Spalding D.B. A calculation procedure for heat, mass and momentum transfer in three-dimensional parabolic flows. International Journal of Heat and Mass Transfer 1972,15: 1787-1806
[11] Menter F.R. , Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications, 1994, AIAA Journal, vol. 32, no 8. pp. 1598-1605.
[12] Katz J, Plotkin A. Low Speed Aerodynamics , Cambridge, Cambridge Univ. Press, 2008
[13] XFLR5, http://www.xflr5.com/xflr5.htm, Sep. 2014
[14] Otto F., Rasch B. Finding Form, Deutscher Werkbund Bayern, Edition A, Menges, 1995.
[15] Schek H-J, The force density method for form finding and computations of general networks, Computer Methods in Applied Mechanics and Engineering, 1974, 3:115-134
[16] Wakefield DS, Engineering analysis of tension structures: theory and practice, Engineering Structures, 1999, 21(8): 680-690
[17] Bletzinger K-U., Form finding of tensile structures by the updated reference strategy, In proceedings of the IASS International Collequium Structural Morphology-Towards the New Millennium, Chilton JW et al. (eds), University of Nottingham, U.K., 1997.
[18] W¨uchner, R. and Bletzinger, K.-U. (2005), Stress-adapted numerical form finding of pre-stressed surfaces by the updated reference strategy. Int. J. Numer. Meth. Engng., 64: 143166
[19] W¨uchner, R., Kupzok, A. and Bletzinger, K.-U. (2007), A framework for stabilized partitioned analysis of thin membranewind interaction. Int. J. Numer. Meth. Fluids, 54: 945963
[20] Bertagnolio F, Sorensen N, Johansen J ,Profile Catalogue for Airfoil Sections Based on 3D Computations, Riso National Laboratory, 2006