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• W2321886299 abstract "Large-eddy simulations were carried out in order to explore flow control strategies for a high-lift wing section. The configuration consisted of a baseline laminar flow geometry, with smoothly deflected leading and trailing-edge flaps, that were are deployed at a 45 deg angle with respect to the undeflected state. In previous investigations of the NASA based design, continuous blowing from internal plenums was utilized to mitigate transition, increase attached flow, and enhance lift. While that approach was successful, it required a substantial amount of mass flow to improve performance. The current effort examines alternative control systems that may be more energy efficient. Solutions were obtained to the Navier-Stokes equations, at the experimental chord-based Reynolds number of 1.0×10 and Mach number of 0.14. The numerical method is based upon a high-fidelity scheme and an implicit time-marching approach. An overset mesh system was employed to represent blowing nozzles interior to the wing surface. Simulations considered two different angles of attack, and control consisting of pulsed blowing and the segmented arrangement of nozzles. Details of the computations are described, effectiveness of the control is quantified, and physical features of the computed flowfields are characterized. Comparisons are provided with baseline cases without control, and with continuous blowing situations, where experimental data is also available. It was found that pulsed blowing can reduce mass flow requirements by more then 30% with minimal loss of lift. For segmented blowing, mass flow was reduced by over 50%, however control was found to be largely ineffective." @default.
• W2321886299 created "2016-06-24" @default.
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• W2321886299 date "2016-01-02" @default.
• W2321886299 modified "2023-09-23" @default.
• W2321886299 title "Control Strategies for a Laminar-Flow Compatible High-Lift Wing Configuration" @default.
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• W2321886299 doi "https://doi.org/10.2514/6.2016-0322" @default.
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