TY - GEN
T1 - Improved delayed detached eddy simulation of agard wing flutter with fully coupled fluid-structure interaction
AU - Patel, Purvic
AU - Zha, Gecheng
N1 - Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - The Shear Stress Transport model based improved delayed detached eddy simulation of the AGARD Wing 445.6 is performed at the subsonic, transonic and supersonic flow with high order shock capturing schemes. An implicit unfactored Gauss-Seidel line iteration scheme is used to solve the compressible, filtered Navier-Stokes equations. The flow solver and the modal form structural solver utilize the dual time-stepping scheme to achieve fully coupled fluid-structural interaction via successive iterations using a pseudo time step. The LES sub-grid length scale based on the vorticity aligned with a grid line is used to overcome the standard sub-grid length scale’s delayed flow transition problem. The predicted flutter boundary agrees well with the experiment at different Mach numbers, including the supersonic flow where the traditional RANS methods over-predict the flutter velocity index and frequency. At the transonic and supersonic flow, the torsional mode generalized displacement is decreased due to the shock oscillations over the suction and pressure surface of the wing. At the flutter boundary, no flow separation is observed at different Mach numbers.
AB - The Shear Stress Transport model based improved delayed detached eddy simulation of the AGARD Wing 445.6 is performed at the subsonic, transonic and supersonic flow with high order shock capturing schemes. An implicit unfactored Gauss-Seidel line iteration scheme is used to solve the compressible, filtered Navier-Stokes equations. The flow solver and the modal form structural solver utilize the dual time-stepping scheme to achieve fully coupled fluid-structural interaction via successive iterations using a pseudo time step. The LES sub-grid length scale based on the vorticity aligned with a grid line is used to overcome the standard sub-grid length scale’s delayed flow transition problem. The predicted flutter boundary agrees well with the experiment at different Mach numbers, including the supersonic flow where the traditional RANS methods over-predict the flutter velocity index and frequency. At the transonic and supersonic flow, the torsional mode generalized displacement is decreased due to the shock oscillations over the suction and pressure surface of the wing. At the flutter boundary, no flow separation is observed at different Mach numbers.
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M3 - Conference contribution
AN - SCOPUS:85100320595
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 16
BT - AIAA Scitech 2021 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -