The effects of a full-aircraft aerodynamic model on the design of a tailored composite wing

Abstract

This paper discusses the effects of the aerodynamic model on the design of a composite wing via aeroelastic tailoring. The classic framework for analysis and optimization of composite wings developed at Delft University of Technology adopts panel method aerodynamics to calculate static and dynamic loads. The current work expands the aerodynamic model by including fuselage and horizontal tail. The non-linear trim condition is thus calculated taking into account both moment and force equilibrium. The effect the fuselage and horizontal tail have on the load distribution, and relative position between the aerodynamic center and the center of gravity translate into different tailored designs for the composite wings. This study provides insights regarding the use of a full-aircraft aerodynamic model for aeroelastic tailoring optimization.