Corey Abe

Abstract

The aerodynamic performance of airfoils operating at Reynolds numbers below 105 has been of interest due to its variety of applications in areas such as unmanned remotely piloted vehicles, small-scale machinery, and more recently, Micro Air Vehicles (MAV's). Design and testing of airfoils to meet these applications is challenging due to the lack of experimental data in low Reynolds flow, compared to airfoils tested at higher Reynolds numbers. Two mechanical balance devices are designed and evaluated to provide a quick and simple method to test small airfoil aerodynamic loads. Each device measures two degrees of freedom; a force balance measures lift and drag forces and a moment balance measures pitch and roll moments. Coefficients of lift and drag vs. angle of attack and coefficients of pitch and roll vs. angle of attack or sideslip angle data are obtained from the fabricated devices and compared to literature results. A statistical evaluation is performed on various aspect ratio flat plate and cambered airfoils to test repeatability. Testing procedures are documented and an overall analysis of testing methods and device designs are discussed.

Library of Congress Subject Headings

Aerodynamic load; Aerofoils--Testing; Reynolds number

Publication Date

12-1-2003

Document Type

Thesis

Department, Program, or Center

Mechanical Engineering (KGCOE)

Advisor

Kochersberger, Kevin

Advisor/Committee Member

Kozak, Jeffery

Advisor/Committee Member

Ghosh, Amitabha

Comments

Note: imported from RIT’s Digital Media Library running on DSpace to RIT Scholar Works. Physical copy available through RIT's The Wallace Library at: TL574.P7 A23 2003

Campus

RIT – Main Campus

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