Print Email Facebook Twitter Aeroelastic response of an aircraft wing to random loads Title Aeroelastic response of an aircraft wing to random loads Author Lee, B.H.K. Institution National Research Council Canada, National Aeronautical Establishment, High Speed Aerodynamics Laboratory Date 1983-04-30 Abstract A method for the prediction of the response of an elastic wing to random loads at flight conditions using rigid model wind tunnel pressure fluctuation measurements is presented. The wing is divided into panels or elements, and the load is computed from measured pressure fluctuations at the centre of each panel. A series representation with terms of the correlated noise type is used to curve fit the experimentally determined pressure power spectra. Two methods are used to calculate the random load spectrum: a constant correlation approximation, and an exponential spatially decaying cross-power spectrum model for the pressure. The coupling between the structural dynamics and aerodynamics of a vibrating wing is taken into consideration using the doublet-Iattice method for computing the unsteady aerodynamic forces. The acceleration and displacement response spectra have been computed for the F -4E aircraft for various Mach numbers, dynamic pressures and flight altitudes. The importance of the unsteady aerodynamic loads induced by the vibration of the wing and input load representation is illustrated by comparing the theoretical predictions with results from flight tests. To reference this document use: http://resolver.tudelft.nl/uuid:8a486702-2af0-40b3-9092-f23a2ca6c7dd Publisher National Research Council Canada Access restriction Campus only Source National Research Council Aeronautical Report LR 613; NRC No. 21230 Part of collection Aerospace Engineering Reports Document type report Rights (c) 1983 National Research Council Canada Files PDF LR-613.pdf 5.98 MB Close viewer /islandora/object/uuid:8a486702-2af0-40b3-9092-f23a2ca6c7dd/datastream/OBJ/view