Comparison of pneumatic jets and tabs for Active Aerodynamic Load Control
Article first published online: 13 JUN 2013
Copyright © 2013 John Wiley & Sons, Ltd.
Volume 17, Issue 9, pages 1365–1384, September 2014
How to Cite
2014), Comparison of pneumatic jets and tabs for Active Aerodynamic Load Control, Wind Energ., 17, 1365–1384, doi: 10.1002/we.1638, , , and (
- Issue published online: 7 AUG 2014
- Article first published online: 13 JUN 2013
- Manuscript Accepted: 24 APR 2013
- Manuscript Revised: 14 FEB 2013
- Manuscript Received: 22 JUL 2011
- National Defense Science and Engineering Graduate Fellowship
- unsteady aerodynamics;
- load control;
- normal surface blowing;
A fast, efficient way to control loads on utility scale wind turbines is important for the growth of the wind industry. Microtabs and microjets are two Active Aerodynamic Load Control devices, which address this need. Both act perpendicular to the surface of the airfoil, and these actively controlled devices are used to mitigate changes in aerodynamic loading experienced by wind turbine rotors due to wind gusts, wind shear, or other atmospheric phenomena. This work explores the aerodynamic effects of microjets and then compares them to those of microtabs. Flow around an airfoil with an activated microjet at the trailing edge has been simulated using the Reynolds-averaged Navier–Stokes solver OVERFLOW-2. Using a Chimera overset grid topology, a microjet has been placed near the trailing edge of the lower surface of a NACA 0012 airfoil. For a jet velocity about half of the freestream velocity, the microjet can change the lift up to ΔCL = 0.2, but the amount of change varies with the momentum coefficient of the jet. The change in lift is not symmetric for positive and negative angles of attack due to changes in the boundary layer thickness with angle of attack. Increasing the Reynolds number reduces the effectiveness of the microjet only slightly. The effects of jet velocity, jet activation time, and airfoil angle of attack on airfoil lift, drag, and pitching moment are compared with previous work, which illustrates the deployment of a microtab at the 95% chord location of a NACA 0012 airfoil. This study shows that microjets and microtabs have very similar responses in lift and pitching moment, but the drag for the microjet is noticeably lower. Copyright © 2013 John Wiley & Sons, Ltd.