The enhancement of high altitude drone endurance compels to design very flexible high-aspect-ratio composite airframe vulnerable to destructive fluid/structure interaction like flutter or torsional divergence. Extensive research has been conducted to increase critical speed without being at the expense of weight balance, one of the promising solutions is the aeroelastic tailoring which consists in a specific configuration of laminated composite layup. The present work presents an aeroelastic reduced order model suitable for the non linear anisotropic behavior of this kind of composite wing implemented in Fortran and Python using optimised open source solver. Along with validation test cases, a simple composite laminate specimen simulation is presented to assess aeroelastic tailoring effect.