This study presents the first 3D two-way coupled fluid structure interaction (FSI) simulation of a hybrid anechoic wind tunnel (HAWT) test section with modeling all important effects, such as turbulence, Kevlar wall porosity and deflection, and reveals for the first time the complete 3D flow structure associated with a lifting model placed into a HAWT. The Kevlar deflections are captured using finite element analysis (FEA) with shell elements operated under a membrane condition. Three-dimensional RANS CFD simulations are used to resolve the flow field. Aerodynamic experimental results are available and are compared against the FSI results. Quantitatively, the pressure coefficients on the airfoil are in good agreement with experimental results. The lift coefficient was slightly underpredicted while the drag was overpredicted by the CFD simulations. The flow structure downstream of the airfoil showed good agreement with the experiments, particularly over the wind tunnel walls where the Kevlar windows interact with the flow field. A discrepancy between previous experimental observations and juncture flow-induced vortices at the ends of the airfoil is found to stem from the limited ability of turbulence models. The qualitative behavior of the flow, including airfoil pressures and cross-sectional flow structure is well captured in the CFD. From the structural side, the behavior of the Kevlar windows and the flow developing over them is closely related to the aerodynamic pressure field induced by the airfoil. The Kevlar displacement and the transpiration velocity across the material is dominated by flow blockage effects, generated aerodynamic lift, and the wake of the airfoil. The airfoil wake increases the Kevlar window displacement, which was previously not resolved by two-dimensional panel-method simulations. The static pressure distribution over the Kevlar windows is symmetrical about the tunnel mid-height, confirming a dominantly two-dimensional flow field.
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Limit Cycle Oscillation Suppression Using a Closed-loop Nonlinear Active Flow Control Technique
This paper presents a nonlinear control method,
which achieves simultaneous fluid flow velocity control and
limit cycle oscillation (LCO) suppression in a flexible airfoil.
The proposed control design is based on a dynamic model
that incorporates the fluid structure interactions (FSI) in the
airfoil. The FSI describe how the flow field velocity at the
surface of a flexible structure gives rise to fluid forces acting
on the structure. In the proposed control method, the LCO
are controlled via control of the flow field velocity near the
surface of the airfoil using surface-embedded synthetic jet
actuators. Specifically, the flow field velocity profile is driven to a
desired time-varying profile, which results in a LCO-stabilizing
fluid forcing function acting on the airfoil. A Lyapunov-based
stability analysis is used to prove that the active flow control
system asymptotically converges to the LCO-stabilizing forcing
function that suppresses the LCO. Numerical simulation results
are provided to demonstrate the performance of the proposed
active flow-and-LCO suppression method.
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- Award ID(s):
- 1809790
- NSF-PAR ID:
- 10250502
- Date Published:
- Journal Name:
- IEEE Conference on Decision and Control
- Page Range / eLocation ID:
- 5507 to 5512
- Format(s):
- Medium: X
- Sponsoring Org:
- National Science Foundation
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- Free Publicly Accessible Full Text
-
Accepted Manuscript1.0
- Conference Paper:
- https://doi.org/10.1109/CDC42340.2020.9303839
