Theoretical and Experimental Flutter Predictions in High Aspect Ratio Composite Wings 2011-01-2722

Next generation of composite civil aircrafts and unconventional configurations, such as High Altitude Long Endurance HALE-UAV, exhibit aeroelastic instabilities quite different from their rigid counterparts. Consequently, one has to deal with phenomena not usually considered in classical aircraft design. Alternative design criteria are needed in order to maintain the safety levels imposed by the regulations and required for certification. The A2-Net-Team project aims to build a multi-disciplinary network of researchers with complementary expertise to develop analytical methods used for a better understanding and assessment of the factors contributing to the occurrence of critical aeroservoelastic instabilities. Along with modeling and numerical investigations a test article will also provide the opportunity to modify and calibrate theoretical models, to highlight and explore their limits, to recommend the necessary modifications and future pertinent investigations. The objective of this paper is to provide the authors' point of view on a consistent scaling procedure applicable when investigating the flutter stability of a full-size high aspect-ratio composite wing structure by means of an economical laboratory wind tunnel test model. Sizing and technological development aspects are discussed along with a detailed design procedure to gather the necessary data for the model manufacture. To exemplify the procedure a wooden model is fabricated and used to provide insight into the scaling procedure and verify the acquired data. Finally a dynamically scaled composite model is defined for a wind tunnel aeroelastic test.