Research Information System
Journal of Aircraft, vol.47, no.6, pp.2067-2074, 2010 (SCI-Expanded)
Static aeroelastic analysis of an adaptive camber wing subjected to low-speed subsonic flow is presented. In finite element modeling follower forces, geometric nonlinearity, and contact definitions are included to accurately integrate a previously designed hingeless control surface into the wing. Camber variation is controlled at six spanwise stations using actuators for which actuation force magnitudes are determined iteratively using linearized influence coefficients. Flow solutions are obtained using a high-order panel method, and aeroelastic coupling is performed using the in-house code SAMOA. For morphed-wing configurations, induced drag is reduced by creating washout. By conducting static aeroelastic analysis actuation, force magnitudes are determined and favorable aerodynamic effects are identified. Results indicate that use of a nonlinear structural model is essential in capturing the stiffening behavior observed during application of spanwise variable camber. Copyright © 2010.