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Aeroelastic Analysis of SUGAR Truss-Braced Wing Wind-Tunnel Model Using FUN3D and a Nonlinear Structural ModelConsiderable attention has been given in recent years to the design of highly flexible aircraft. The results of numerous studies demonstrate the significant performance benefits of strut-braced wing (SBW) and trussbraced wing (TBW) configurations. Critical aspects of the TBW configuration are its larger aspect ratio, wing span and thinner wings. These aspects increase the importance of considering fluid/structure and control system coupling. This paper presents high-fidelity Navier-Stokes simulations of the dynamic response of the flexible Boeing Subsonic Ultra Green Aircraft Research (SUGAR) truss-braced wing wind-tunnel model. The latest version of the SUGAR TBW finite element model (FEM), v.20, is used in the present simulations. Limit cycle oscillations (LCOs) of the TBW wing/strut/nacelle are simulated at angle-of-attack (AoA) values of -1, 0 and +1 degree. The modal data derived from nonlinear static aeroelastic MSC.Nastran solutions are used at AoAs of -1 and +1 degrees. The LCO amplitude is observed to be dependent on AoA. LCO amplitudes at -1 degree are larger than those at +1 degree. The LCO amplitude at zero degrees is larger than either -1 or +1 degrees. These results correlate well with both wind-tunnel data and the behavior observed in previous studies using linear aerodynamics. The LCO onset at zero degrees AoA has also been computed using unloaded v.20 FEM modes. While the v.20 model increases the dynamic pressure at which LCO onset is observed, it is found that the LCO onset at and above Mach 0.82 is much different than that produced by an earlier version of the FEM, v. 19.
Document ID
20150006030
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Bartels, Robert E. (NASA Langley Research Center Hampton, VA, United States)
Scott, Robert C. (NASA Langley Research Center Hampton, VA, United States)
Allen, Timothy J. (Boeing Research and Technology Huntington Beach, CA, United States)
Sexton, Bradley W. (Boeing Research and Technology United States)
Date Acquired
April 21, 2015
Publication Date
January 5, 2015
Subject Category
Aerodynamics
Structural Mechanics
Report/Patent Number
NF1676L-18975
Meeting Information
Meeting: AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
Location: Kissimmee, FL
Country: United States
Start Date: January 5, 2015
End Date: January 9, 2015
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 432938.11.01.07.43.40.08
Distribution Limits
Public
Copyright
Public Use Permitted.

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