Transonic Aeroelastic Numerical Simulationin Aeronautical Engineering

摘要

An LU-SGS (lower-upper symmetric Gauss-Seidel)rnsubiteration scheme is constructed for time-marchingrnof the fluid equations. The HLLEW (Harten-Lax-vanrnLeer-Einfeldt-Wada) scheme is used for the spatialrndiscretization. The same subiteration formulation isrnapplied directly to the structural equations of motion inrngeneralized coordinates. Through subiteration betweenrnthe fluid and structural equations, a fully implicitrnaeroelastic solver is obtained for the numericalrnsimulation of fluid/structure interaction. To improve thernability for application to complex configurations, arnmultiblock grid is used for the flow field calculationrnand Transfinite Interpolation (TFI) is employed for thernadaptive moving grid deformation. The infinite platernspline (IPS) and the principal of virtual work arernutilized for the data transformation between the fluidrnand structure. The developed code was first validatedrnthrough the comparison of experimental andrncomputational results for the AGARD 445.6 standardrnaeroelastic wing. Then the flutter character of a tailrnwing with control surface was analyzed. Finally, flutterrnboundaries of a complex aircraft configuration werernpredicted.