Lock-in of Elastically Mounted Airfoils at High Angles of Attack
Conference Paper
Overview
Identity
Other
View All
Overview
abstract
Vortex-induced vibration of elastically mounted cylinders has been researched extensively due to applications in the petroleum, nuclear, and civil engineering fields. One simple method of reducing vibrations is streamlining the cylinder into an airfoil shape. However, if flow direction changes, an elastic airfoil could experience similar oscillations. To better understand a general airfoil's response, three elastically mounted airfoil shapes are tested at a 90 angle of attack. The shapes are a NACA 0018, a sharp leading and trailing edge (sharp-sharp model), a round leading and trailing edge (round-round model), and a cylinder as a control. The NACA 0018 and sharp-sharp configuration show nearly identical responses, indicating a single sharp edge characterizes the lock-in response. The cylinder and round-round airfoil have responses over four times larger than the NACA 0018 and sharp-sharp airfoils. Thus, the existence of a sharp edge is critical. The response of the NACA 0018 and round-round decreases linearly with increasing mass ratio, but at different rates. Inconsistent hysteresis is shown for the both the cylinder and round-round airfoil. 2012 by the American Institute of Aeronautics and Astronautics, Inc.
name of conference
50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
