Three dimensional aeroelastic analyses considering free-play nonlinearity using computational fluid dynamics/computational structural dynamics coupling

Most of the previous studies on free-play aeroelasticity were based linear aerodynamic theory, which cannot consider nonlinear effects. This paper proposes a framework computational fluid dynamics/computational structural dynamics (CFD/CSD) coupling approach that can deal with three dimensional aeroelastic problems both nonlinearity and nonlinearity. The fictitious mass method is used to construct reduced equations motion switching point detected using bisection method. adaptive time step obtained by returned CFD solver so are integrated same step. An all-movable wing at root considered for numerical studies. Results demonstrate CFD/CSD predict stable limit cycle oscillation (LCO) effectively. initial condition study shows LCO behavior subcritical hysteresis response be predicted in domain effectively presented viscous effect shown increase boundary shift amplitude larger velocity transonic regime. determined from subsonic Mach numbers. dip found method, but equivalent linearization doublet lattice fails this phenomenon. From results study, 43.5% below flutter most.