복합재료 날개의 천음속/초음속 하중 재분포 해석

Abstract

In this study, the load distribution analysis of a composite Wing has been studied in the transonic and supersonic flow regime. The effects of fiber orientation on the deformation pattern and the aerodvnamic coefficients have been also investioated. Finite element method and computational fluid dynamics using transonic small disturbance equation have been applied for the present coupled aeroelastic analysis. The static aeroelastic analysis of isotropic and composite aircraft wing with two different airfoil shapes have been conducted to consider the nonlinear shock waves in the transonic and supersonic flow regime. The deformation shape and aerodynamic coefficient of a composite wing have been compared for the various laminate angle sets. Analyses conditions have been set up to give the useful data which can be compared with the results of wind tunnel test in the future.