Aerodynamic damping of blade flap motions at high angles of attack
- Univ. of Utah, Salt Lake City, UT (United States). Mechanical Engineering Dept.
The YawDyn computer code is used to calculate the aerodynamic damping for a typical teetering rotor configuration. The code has been modified to calculate the net work done by aerodynamic forces in one complete rotor revolution. All cases were run for a teetering rotor similar to the ESI-80 with a specified teeter angle motion in order to isolate the aerodynamic effects from the inertial and gravitational loads. Effects of nonlinear static stall, dynamic stall, dynamic inflow, and delayed static stall due to rotation stability of flap motions in high winds. Contributions of the various steady and unsteady aerodynamic effects are presented for two airfoils: the LS(1) and the NREL Thin Airfoil Family (S805A, S806, S807). Teeter stability is compared for a blade with 10{degree} of linear twist and a blade with optimum aerodynamic twist.
- OSTI ID:
- 93005
- Report Number(s):
- CONF-950116--; ISBN 0-7918-1294-4
- Country of Publication:
- United States
- Language:
- English
Similar Records
Dynamic stall and aerodynamic damping
A comparison of baseline aerodynamic performance of optimally-twisted versus non-twisted HAWT blades