Revisit of the variable stiffness method for aeroelastic computations with/without thermal effects based on computational fluid dynamics

In the present study, a variable stiffness method (VSM) is revisited for aeroelastic computations with/without thermal effects. Unlike traditional CFD/CSM coupling (TM), which predicts responses by varying freestream conditions (e.g. density, velocity), in VSM can be fixed. The first verified theoretically and adopted to predict nonlinear responses. For computations, applied flutter onset of Isogai wing section limit cycle oscillation (LCO) Goland+ at transonic conditions. structural free-play nonlinearity included system further demonstrate method. computation with effects considered as prediction simply supported panel supersonic flow. It shown that replicate predicted its counterpart under same flow similarity parameters Mach number, Reynolds number), whereby need adjusted. Limitations are also pointed out discussed. To assess VSM, an ARMA model constructed framework demonstrated regime.