Prediction of wing aeroelastic effects on aircraft life and pitching moment characteristicsThe distribution of flight loads on an aircraft structure determine 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 of 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 ID
19880003974
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Eckstrom, Clinton V. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
July 1, 1987
Publication Information
Publication: AGARD Static Aeroelastic Effects on High Performance Aircraft