Limit Cycle Oscillations (LCO) and Nonlinear Aeroelastic Wing Response.
Abstract
Limit cycle oscillations (LCO) have been observed for elastic wings at moderate to high angles of attack where separated flow is thought to occur. At transonic flow conditions with shock waves present, flow separation may occur at moderate angles of attack. For higher angles of attack, separation may occur at (low) subsonic conditions. Empirical quasi steady aerodynamic models based on steady state experimental data have shown some success in predicting the observed LCO. New theoretical aeroelastic models are proposed here to improve the prediction of LCO. Also proposed are simple, flow speed experiments to validate these theoretical models with an option for high speed experiments as well.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 04, 1996
- Accession Number
- ADA325524
Entities
People
- Earl H. Dowell
Organizations
- Duke University