Prediction of Wing Aeroelastic Effects on Aircraft Lift and Pitching Moment Characteristics,
Abstract
The distribution of flight loads on an aircraft structure determines the lift and pitching moment characteristics of the aircraft. When the load distribution changes due to the aeroelastic response of the structure, the lift and pitching moment characteristics also change. An estimate of the effect of aeroelasticity on stability and control characteristics is often required for the development of aircraft simulation models for evaluation of flight characteristics. This presentation outlines a procedure for incorporating calculated linear aeroelastic effects into measured nonlinear lift and pitching moment data from wind tunnel tests. Results are presented which were obtained from applying this procedure to data for an aircraft with a very flexible transport type research wing. The procedure described is generally applicable to all types of aircraft.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 03, 1986
- Accession Number
- ADP005860
Entities
People
- Clinton V. Eckstrom
Organizations
- Langley Research Center