Affordable Rotorcraft Air Vehicle Drag Reduction for Cruise Efficiency and Enhanced Lift Using Plasma Flow Control

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$70,000.00
Award Year:
2010
Program:
SBIR
Phase:
Phase I
Contract:
N00014-09-M-0467
Agency Tracking Number:
N092-144-0581
Solicitation Year:
2009
Solicitation Topic Code:
N092-144
Solicitation Number:
2009.2
Small Business Information
Orbital Research Inc
4415 Euclid Avenue, Suite 500, Cleveland, OH, 44103
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
557510336
Principal Investigator:
Srikanth Vasudevan
Aerospace Engineer
(216) 649-0399
vasudevan@orbitalresearch.com
Business Contact:
Joseph Snyder
Vice President
(216) 649-0399
snyder@orbitalresearch.com
Research Institution:
n/a
Abstract
The V-22 Osprey can benefit from drag reductions in at least two areas: low angle of attack drag reduction will provide an improvement in the cruise efficiency and hover download reduction will provide an increase in cargo capability. Orbital Research, in collaboration with the University of Toledo, proposes to develop an innovative, affordable Plasma-On-Demand (POD) system to reduce the drag of the V-22 during cruise, improve lift characteristics during maneuvers and reduce download in hover. During the Phase I program, Orbital will experimentally demonstrate the effectiveness of strategically placed plasma actuators in novel configurations and compare the effectiveness with existing passive VGs on the V-22 geometry at representative flight Mach numbers. Additionally, in combination with novel actuator configurations, an experimental approach will be used to identify suitable dielectric materials to increase the plasma actuator effectiveness at high speeds. For the Phase I Option program, Orbital will investigate the effectiveness of the plasma actuator arrangements at representative Reynolds numbers via CFD and create a hardware integration plan – highlighting the key components to be considered at a system level.

* information listed above is at the time of submission.

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