Dynamic Stall Flow Control Through the Use of a Novel Plasma Based Actuator Technology

Award Information
Agency:
National Aeronautics and Space Administration
Amount:
$120,492.00
Program:
STTR
Contract:
NNX12CG07P
Solitcitation Year:
2011
Solicitation Number:
N/A
Branch:
N/A
Award Year:
2012
Phase:
Phase I
Agency Tracking Number:
110046
Solicitation Topic Code:
T2.01
Small Business Information
Lynntech, Inc.
2501 Earl Rudder Freeway South, College Station, TX, -
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
184758308
Principal Investigator
 Ashwin Balasubramanian
 Principal Investigator
 (979) 764-2200
 ashwin.balasubramanian@lynntech.com
Business Contact
 G. Renee Hisaw
Title: Business Official
Phone: (979) 764-2218
Email: renee.hisaw@lynntech.com
Research Institution
 The University of Texas at Austin
 Courtney Frazier Swaney
 210 E. 24th Street, WRW
Austin, TX, 78712-0235
 () -
 Domestic nonprofit research organization
Abstract
Lynntech proposes a novel flow control methodology for airfoils undergoing dynamic stall. Dynamic stall refers to an aerodynamic phenomenon that is experienced by airfoils that undergo rapid changes in the flow angle of attack such as rotorcraft based airfoils, flapping wing technologies as well as fixed wing aircrafts undergoing sudden angle of attack changes. Dynamic stall is inherently an unsteady, non linear and complicated effect that can affect such flight parameters as lift, drag and airfoil stability.Lynntech, along with its STTR partner in Dr. Noel Clemens and Dr. Jayant Sirohi, at the University of Texas at Austin proposes to use novel pulsed plasma discharge based actuators for flow control on dynamically stalled airfoils. Lynntech has more than 20 years of experience with applied plasma physics and 10 years of experience with turbulent CFD modeling. Dr. Noel Clemens at the University of Texas Flow Imaging Research Laboratory in the Department of Aerospace Engineering, who has implemented and tested various types of plasma actuators for flow control.The proposed technology consists of pulsed plasma actuators which will induce high velocity airflow within the airfoil boundary layer, thus reattaching the flow. The proposed plasma actuator can achieve high Reynolds number (>5e6) flow control compared to contemporary dielectric barrier discharge plasma actuators without relying on corona discharge / hot plasma technology. Advantages of the system include low power consumption, ease of installation, increased flight stability, reduced drag and higher stall angles.

* information listed above is at the time of submission.

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