PROJECT TITLE: Active Control of Rotor Dynamic Stall
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A program for the development of an active control system for controlling dynamic stall on rotor blades is proposed. The system utilizes an array of pulsed jet actuators near the blade leading edge to control unsteady lift and flow separation during transient pitch-up. The ability to control these processes will alleviate problems which currently limit rotary-wing vehicle performance. The control system, which has previously been tested at low-speed, will be refined and tested on a small-scale rotor blade section mounted in a transonic wind tunnel at Ohio State University. The ability to control and delay dynamic stall events during oscillatory pitching of the model will be evaluated in open-loop experiments. Results from the tests will be used to develop parametric scaling laws to aid in designing an actuator system for full-scale rotors. The experimental results will be used as guidelines for the design of a Phase II prototype control system for large-scale testing at flight conditions.
POTENTIAL COMMERCIAL APPLICATIONS
The performance of both commercial and military rotorcraft will be enhanced through the application of the proposed control system. The system will alleviate rotor blade stall which currently limits high-speed forward flightand produces excessive noise in certain flight regimes. The successful development and application of this control system will result in the design of more versatile and quiet rotorcraft and VSTOL vehicles.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
Keith R. McManus Physical Sciences Inc. 20 New England Business Center Andover , MA 01810 - 1077
NAME AND ADDRESS OF OFFEROR
Physical Sciences Inc. 20 New England Business Center Andover , MA 01810 - 1077