A Coupled Approach for Plasma-Based Flow Control Simulations of Wing Sections
Abstract
Numerical experiments in two- and three-dimensions, performed with a high-fidelity algorithm, are employed to explore plasma-actuator-based control of flow past a stalled NACA 0015 wing section. The time accurate force field from a self-consistent asymmetric-electrode arrangement at 5kHz (continuous wave) is coupled to the Navier-Stokes equations at a nominal Reynolds number of 45, 000 and angle-of-attack of 15o. When the actuator is placed slightly downstream of the separation point, the mean and asymptotic flow response include formation of a wall-jet and inhibition of separation. Features of the unsteadiness directly associated with the forcing, as well as that due to shedding occurring near the trailing edge are delineated. The results suggest that both streamwise and normal (towards the wall) components of force play important roles. A simpler phenomenological model is also employed to examine flow control in the full 3-D setting. At higher Reynolds number, 90, 000, the flow becomes turbulent immediately downstream of the leading edge and remains attached in the mean. The effect of the actuator in this situation is to laminarize the flow together with the formation of a wall-jet. When the actuator location is moved to the point of maximum thickness, laminar separation is induced near the leading edge with subsequent breakdown to turbulence. When stall is observed, at 18 deg angle of attack, placing the actuator near the leading edge yields the anticipated laminar wall jet on the upper surface. The effect of actuator force strength on separation suppression is examined in terms of the combined effect of transition to turbulence and near wall momentum enhancement. Finally, the effect of pulsing is documented at Reynolds number 45, 000 with 20%duty cycle and interpulse periods of 0.7 and 0.25 characteristic times respectively.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 2006
- Accession Number
- ADA594401
Entities
People
- Datta V. Gaitonde
- Miguel R. Visbal
- Subrata Roy
Organizations
- Air Force Research Laboratory