Abstract : One can change the effective shape of a surface without any change in its physical moldlines through the transient injection of momentum to control unsteady flow phenomena, such as separation. This research program consists of a system level evaluation of the potential benefits and costs of active flow control as applied to UAVs for separation control, development of innovative actuator concepts, and proof-of-concept experiments showing aerodynamic effectiveness. System-level benefits include increased gust margin, reduced takeoff field length, increased payload capacity, and greater maneuverability. Actuator research has resulted in two major innovations: the use of pulsed/modulated waveforms to increase the effectiveness of synthetic jet actuators and the development of compact, high power, combustion-driven actuator modules. The general performance of the combustion actuators are characterized in isolation, embedded in cross-flows up to M=0.7, and integrated on a two-dimensional wing model. In addition, since conventional machining would not be suitable for low-cost, large volume production, a simpler, MEMS-based, batch fabrication
[1]
I. Wygnanski,et al.
Delay of Airfoil Stall by Periodic Excitation
,
1996
.
[2]
Uriel Goldberg,et al.
Numerical Simulation of Separation Control via Synthetic Jets
,
2002
.
[3]
K. Zaman,et al.
Effect of acoustic excitation on the flow over a low-Re airfoil
,
1987,
Journal of Fluid Mechanics.
[4]
Jiezhi Wu,et al.
Post-stall flow control on an airfoil by local unsteady forcing
,
1998,
Journal of Fluid Mechanics.
[5]
David E. Parekh,et al.
Combustion-driven jet actuators for flow control
,
2001
.
[6]
Michael Amitay,et al.
CONTROLLED TRANSIENTS OF FLOW REATTACHMENT OVER STALLED AIRFOILS
,
2002,
Proceeding of Second Symposium on Turbulence and Shear Flow Phenomena.