Low Reynolds Number, High-Lift Airfoil Design for VTOL UAVs

Award Information
Agency:
Department of Defense
Branch
Army
Amount:
$69,751.00
Award Year:
2006
Program:
SBIR
Phase:
Phase I
Contract:
W911W6-07-C-0013
Agency Tracking Number:
A062-006-0333
Solicitation Year:
2006
Solicitation Topic Code:
A06-006
Solicitation Number:
2006.2
Small Business Information
AIRFOILS, INCORPORATED
122 Rose Drive, Port Matilda, PA, 16870
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
806623562
Principal Investigator:
Dan Somers
President
(814) 357-0500
dan@airfoils.com
Business Contact:
Dan Somers
President
(814) 357-0500
dan@airfoils.com
Research Institution:
n/a
Abstract
A complementary, theoretical and experimental effort to design and verify high-lift, low pitching-moment airfoils for VTOL UAVs is proposed. In Phase I, an accurate, rapid, test capability will be validated over the range of Reynolds numbers from 50,000 to 500,000 by investigating the E 387 airfoil, the low Reynolds number calibration standard, in The Pennsylvania State University Low-Speed, Low-Turbulence Wind Tunnel. The E 387 airfoil exhibits almost all the pertinent phenomena over the Reynolds number range of interest, making it a sensitive test case, particularly with respect to turbulence effects, a key issue for VTOL UAVs. The section characteristics measured with transition free and fixed will be compared with results from other low-turbulence wind tunnels and with predictions from the Eppler and XFOIL/MSES codes. The initial specifications for the airfoils to be designed in Phase II will be defined in cooperation with U.S. Army personnel. In Phase II, the experimental results will be used to refine existing airfoil design and analysis methods and for CFD code validation. A set of airfoils will be tailored to VTOL UAV applications and experimentally verified. The slotted, natural-laminar-flow (SNLF) airfoil concept will be adapted to VTOL UAV applications.

* information listed above is at the time of submission.

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