Aiaa 96-2517-Cp Twin Tail/Delta Wing Configuration Buffet
AIAA 96-2517-CP TWIN TAIL/DELTA WING CONFIGURATION BUFFET DUE TO UNSTEADY VORTEX BREAKDOWN FLOW Osama A. Kandil, Essam F. Sheta and Steven J. Massey Aerospace Engineering Department Old Dominion University Norfolk, VA 23529 The 14th AIAA Applied Aerodynamics Conference New Orleans, LA-June 18-20, 1996 I | For Permission to copy or republish, contact the American Institute of Aeronautics and Astronautics 370 12Enfant Promenade, S. W., Washington, D.C. 20024 / NASA-CR-203259 o J _"_G"7"_ COMPUTATION AND VALIDATION OF FLUID/ STRUCTURE TWIN TAIL BUFFET RESPONSE Osama A. Kandil and Essam F. Sheta Aerospace Engineering Department Old Dominion University, Norfolk, VA 23529, USA C. H. Liu Aerodynamics Methods and Acoustics Branch NASA Langley Research Center, Hampton, VA 23665, USA EUROMECH COLLOQUIUM 349 STRUCTURE FLUID INTERACTION IN AERONAUTICS Institute Fiir Aeroelastik, GSttingen, Germany September 16-18, 1996 COMPUTATION AND VALIDATION OF FLUID/STRUCTURE TWIN TAIL BUFFET RESPONSE Osama A. Kandil 1 and Essam F. Sheta: Aerospace Engineering Department Old Dominion University, Norfolk, VA 23529, USA and C. H. Liu 3 Aerodynamics Methods and Acoustics Branch NASA Langley Research Center, Hampton, VA 23665, USA ABSTRACT The buffet response of the flexible twin-tail/delta wing configuration-a multidisciplinary problem is solved using three sets of equations on a multi-block grid structure. The first set is the unsteady, compressible, full Navier-Stokes equations which are used for obtaining the flow-filed vector and the aerodynamic loads on the twin tails. The second set is the coupled aeroelastic equations which are used for obtaining the bending and torsional deflections of the twin tails.
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