This thesis investigates the effects of biologically inspired leading-edge protuberances on
aircraft wings. The study of humpback whales and their flipper performance was the impetus to
modifying the leading edge of an aircraft wing in order to gain an aerodynamic advantage during
flight. This study examines the effect of leading-edge modification on wing performance at a low
Reynolds number (Re), since low Reynolds number flows have unique features, and the
knowledge about this flight regime is extremely important for small aircraft, called unmanned
aerial vehicles (UAVs), flying at low speeds.
Simulations were executed on wings with leading-edge sinusoidal protuberances, in order to compare the lift and drag characteristics with that of a wing with a smooth leading edge. All wings had the same cross section of National Advisory Committee for Aeronautics (NACA) 2412 and a simulated Reynolds number of 5.7 * 10^5. Results from numerical simulations revealed that a decrease in lift and an increase in drag was observed at low angles of attack (AoA) in all cases of the modified wings. At higher angles (α ≥16º), the lift of the modified wings was up to 48% greater than the baseline wing, with 44% less drag or no drag penalty. The amplitude of protuberances significantly affects wing performance. Although the maximum lift generated by modified wings was lower than baseline, protuberances along the leading edge of the wing proved to have a profound advantage in obtaining higher lift at high angles of attack. / Thesis (M.S.)--Wichita State University, College of Engineering, Dept. of Aerospace Engineering.
| Identifer | oai:union.ndltd.org:WICHITA/oai:soar.wichita.edu:10057/5039 |
| Date | 07 1900 |
| Creators | Malipeddi, Anil Kumar |
| Contributors | Hoffmann, Klaus A. |
| Publisher | Wichita State University |
| Source Sets | Wichita State University |
| Language | en_US |
| Detected Language | English |
| Type | Thesis |
| Format | xiv, 69 p. |
| Rights | © Copyright 2011 by Anil Kumar Malipeddi. All rights reserved |
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