Numerical Investigation of Plasma-Based Control for Low-Reynolds-Number Airfoil Flows

摘要: Large-eddy simulations are carried out to investigate the use of plasma-based actuation for control flows over a finite span wing at low Reynolds numbers. The section corresponds SD7003 airfoil, which is representative those employed micro air vehicle applications. Dielectric-barrier-discharge plasma actuators used modify transitional flow and improve aerodynamic performance. Solutions obtained Navier-Stokes equations, were augmented by source terms represent plasma-induced body forces imparted on fluid. Simple phenomenological models provided generated electric field surrounding actuators. numerical method based upon high-fidelity time-implicit scheme, an implicit large-eddy-simulation approach, domain decomposition in order perform calculations parallel computing platform. Flow chord-based number 40,000 considered investigation, characterized laminar separation suction surface angles attack. This then promotes transition more complex state, can be modified actuation. Several aspects examined, including different actuator configurations, alternative plasma-force models, both continuous pulsed modes operation, magnitude force required control.