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By P. Lorber, D. Mccormick, T. Anderson, B. Wake, D. Macmartin, M. Pollack, T. Corke, K. Breuer, Peter F. Lorber, Duane C. Mccormick, Torger J. Anderson, Brian E. Wake, Douglas G. Macmartin, Michael J. Pollack, Thomas C. Corke and Kenneth Breuer


Abstract * Flow control to avoid or delay rotorcraft retreating blade stall can be an enabling technology for future high performance rotorcraft. Aerodynamic experiments and computations have indicated that appropriate unsteady excitation can delay boundary layer separation and stall on airfoils. Work is in progress to determine the control requirements for helicopter rotor blades at full scale Mach numbers, Reynolds numbers, and with unsteady pitching motions. Compact, powerful, and efficient flow actuation and control systems will be needed. Three actuation concepts were favorably evaluated during initial studies: electromechanical directed synthetic jets (DSJ), periodic flow modulation, and plasma actuation. Electromechanical DSJ and plasma actuators are being developed further and will be evaluated in full scale pitching blade section experiments. These experiments will determine the required control authority, validate the actuator concepts, and study open and closed loop control approaches. Computational studies are being performed of the combined external and actuator flow fields to determine preferred actuation geometries and operating points. System analyses are being used to quantify the benefits for representative aircraft configurations and missions. Copyright ÿ2000 by United Technologie

Year: 2000
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