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Proceedings Paper

MEMS actuators for boundary layer control of micro-rotor blades
Author(s): Nikhil A. Koratkar; Theodorian Borca-Tasciuc
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Paper Abstract

This paper presents on-going research directed towards the development of MEMS actuators for improved aerodynamic efficiency of micro-rotorcraft. A 6 inches diameter micro-rotor system was developed and tested in hover. Results indicated that profile power losses associated with low Reynolds number viscous flows and flow separation and stall at high angles of attack limit the rotor performance at micro-scale. It is envisaged that tripping the flow from laminar to turbulent at the leading edge of the rotor blade can prevent formation of the laminar separation bubble and improve lifting efficiency of the micro-rotor. This study will present the design of a prototype MEMS actuator (piezoelectric thin film). It is envisaged that multiple arrays of such MEMS devices can be assembled on the surface of the airfoil section to create a smart skin. The smart skin when actuated provides controllable surface roughness that can be used to enable premature boundary layer transition.

Paper Details

Date Published: 15 July 2002
PDF: 12 pages
Proc. SPIE 4701, Smart Structures and Materials 2002: Smart Structures and Integrated Systems, (15 July 2002); doi: 10.1117/12.474660
Show Author Affiliations
Nikhil A. Koratkar, Rensselaer Polytechnic Institute (United States)
Theodorian Borca-Tasciuc, Rensselaer Polytechnic Institute (United States)


Published in SPIE Proceedings Vol. 4701:
Smart Structures and Materials 2002: Smart Structures and Integrated Systems
L. Porter Davis, Editor(s)

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