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An advanced carbon fiber is expected to reduce the structural weight of a composite aircraft. Historically, various studies on composite aircraft designs have focused on the challenge to utilize the anisotropy of unidirectional laminates. However, there is still a research interest to consider the impact of changing the fibers for their positive influence on the structural weight and performances of a composite aircraft. In this study, the effects of fiber properties on the static aeroelastic design of aircraft wings were investigated using a multi-scale framework and two-way coupled aeroelastic analysis with structural sizing. The fibers analyzed were T700S, T800S, and T1100G, which have different stiffnesses and strengths. The design analysis was performed under two scenarios: fixing the angle of attack and fixing the lift while changing the angle of attack in the flow condition. The results from the former case indicate that the choice of fiber did not significantly affect the entire shape of the drag polar, while the highest lift coefficient was obtained with the stiffest fiber, T1100G, under the same angle of attack. The results from the latter case indicate that using T1100G can reduce the structural weight by 9.9% and 14% at the same lift compared to T800S and T700S, respectively, owing to its high buckling resistance and high tensile strength, rather than compressive strength.
Date et al. (Fri,) studied this question.