Accession Number : ADP005860

Title :   Prediction of Wing Aeroelastic Effects on Aircraft Lift and Pitching Moment Characteristics,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Personal Author(s) : Eckstrom, Clinton V.

Report Date : 03 OCT 1986

Pagination or Media Count : 17

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.

Descriptors :   *AEROELASTICITY, WINGS, FLIGHT LOADS, LOAD DISTRIBUTION, PREDICTIONS, AERODYNAMIC LIFT, PITCH(MOTION), MOMENTS, STRUCTURAL RESPONSE, STATICS, FLEXURAL PROPERTIES, DYNAMIC PRESSURE, WIND TUNNEL TESTS, EXPERIMENTAL DATA, AERODYNAMIC STABILITY.

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE