Characterization of the Effects of Sweep at Low Reynolds Number
Faculty Mentor Name
Lance Traub
Format Preference
Poster
Abstract
This project is an investigation of wing sweep at low Reynolds numbers. Sweep is the offset of the wing from the direction of flow and the Reynolds number determines the type of fluid flow at specific speeds. The research idea is founded on the growing popularity of small-scale drones. Both unmanned aerial vehicles (UAVs) and micro air vehicles (MAVs) have seen a steady increase in use and application. Efficient design of UAVs and MAVs requires a better understanding of their associated aerodynamics. This need has contributed to an increase in research regarding various wing designs at low Reynolds number and has promoted an understanding of their aerodynamic behavior. For the project, the effects of wing sweep were examined on a series of wings. The wings, comprised of two different airfoil profiles, were manufactured with leading edge sweep angles ranging from 0 to 45 degree. Testing encompassed experimental load measurement at Reynolds numbers ranging from 40,000 to 80,000. The expected outcome is the characterization of the performance of these wing geometries. The investigation will determine the effect of sweep at low Reynolds number. Sweep is expected to increase wing efficiency and performance by improving various performance parameters.
Characterization of the Effects of Sweep at Low Reynolds Number
This project is an investigation of wing sweep at low Reynolds numbers. Sweep is the offset of the wing from the direction of flow and the Reynolds number determines the type of fluid flow at specific speeds. The research idea is founded on the growing popularity of small-scale drones. Both unmanned aerial vehicles (UAVs) and micro air vehicles (MAVs) have seen a steady increase in use and application. Efficient design of UAVs and MAVs requires a better understanding of their associated aerodynamics. This need has contributed to an increase in research regarding various wing designs at low Reynolds number and has promoted an understanding of their aerodynamic behavior. For the project, the effects of wing sweep were examined on a series of wings. The wings, comprised of two different airfoil profiles, were manufactured with leading edge sweep angles ranging from 0 to 45 degree. Testing encompassed experimental load measurement at Reynolds numbers ranging from 40,000 to 80,000. The expected outcome is the characterization of the performance of these wing geometries. The investigation will determine the effect of sweep at low Reynolds number. Sweep is expected to increase wing efficiency and performance by improving various performance parameters.