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Title:Experimental wind tunnel study of airfoils with large flap deflections at low Reynolds numbers
Author(s):Williamson, Gregory
Advisor(s):Selig, Michael S.
Department / Program:Aerospace Engineering
Discipline:Aerospace Engineering
Degree Granting Institution:University of Illinois at Urbana-Champaign
Degree:M.S.
Genre:Thesis
Subject(s):low Reynolds numbers
low Reynolds number airfoils
low Reynolds number airfoil design
low Reynolds number inverse airfoil design
large flap deflections
plain flap
plain flaps at low Reynolds numbers
trailing edge plain flap
symmetrical airfoils
PROFOIL
MFOIL
XFOIL
percent chord flap
flap-chord ratio
flap chord ratio
Reynolds number effects
Reynolds number effects at low Reynolds numbers
airfoil thickness effects at low Reynolds numbers
effects of flap deflection on airfoil performance
effects of flap deflection on airfoil performance at low Reynolds numbers
lift increment
moment increment
maximum lift with a plain flap at low Reynolds numbers
drag measurements for large flap deflections at low Reynolds numbers
lift-to-drag characteristics for airfoils at low Reynolds number with large flap deflections
inverse airfoil design
conformal mapping
AG455ct-02r
AG40d-02r
AG455ct
AG40d
W1011
W1015
E387
Eppler E387
aerobatic airfoils
wind tunnel study at low Reynolds numbers
Low-Speed Airfoil Tests (LSATs)
UIUC LSATs
experimental wind tunnel study of airfoils at low Reynolds numbers with large flap deflections
experimental wind tunnel study of airfoils at low Reynolds numbers
laminar separation bubble
effects of laminar separation bubbles on airfoil performance
effects of laminar separation bubbles on airfoil performance at low Reynolds numbers
boundary layer trip
boundary layer trips at low Reynolds numbers
University of Illinois Urbana-Champaign (UIUC)
Abstract:Lift, drag, and moment measurements were taken at low Reynolds numbers for four airfoils with trailing edge plain flaps in an attempt to understand the effects of Reynolds number, percent thickness (t/c), percent chord of flap (flap-chord ratio), and flap deflection on airfoil performance. The four airfoils used in this research were the AG40d-02r, AG455ct-02r, W1011, and W1015. The W1011 and W1015 are symmetrical airfoils that were design using PROFOIL specifically for this research. PROFOIL is an inverse airfoil design code that utilizes conformal mapping. The W1011 and W1015 were designed to have similar performance characteristics that favor aerobatic flight. Airfoil performance was predicted computationally using XFOIL during the inverse design of the W1011 and W1015 airfoils. In order to effectively analyze and compare the experimental results, lift and moment increment plots were created. Drag data with large flap deflections was collected to determine the main driving factor for airfoil drag in this regime. Flap deflections ranged from -20 to 65 deg and Reynolds numbers varied from 100,000 to 500,000 depending on the airfoil being tested. The flap sizes tested for this research ranged from 20 to 30 percent of chord depending on the airfoil being tested.
Issue Date:2012-05-22
URI:http://hdl.handle.net/2142/31060
Rights Information:Copyright 2012 by Gregory A. Williamson. All rights reserved.
Date Available in IDEALS:2012-05-22
Date Deposited:2012-05


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