Olinger, David J.
Engineering Laboratory Design, Inc
This project investigated aspect ratio and Reynolds number effects on the lift and drag coefficients of flat plate airfoils. Experiments conducted at Reynolds numbers of 50,000, 100,000 and 200,000, angles of attack of 0-30 degrees, and a thickness-to-chord ratio of 1/24 (0.04167) indicated surprising trends. Low aspect ratios yielded high lift/drag ratios, indicating higher efficiency than higher aspect ratio wings. The same wings also demonstrated an increase in stall angle from 8 to 15 degrees, and a corresponding decrease in dCl/da.
Worcester Polytechnic Institute
Major Qualifying Project
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