Non-Intrusive Polynomial Chaos Approach for Nonlinear Aeroelastic Uncertainty Quantification
Presented is a point collocation non-intrusive polynomial chaos approach for nonlinear aeroelastic uncertainty quantification analysis. A unique aspect of our approach is that we are using a nonlinear frequency-domain harmonic balance aeroelastic solution methodology, which allows us to solve directly for a limit cycle oscillation response amplitude versus reduced velocity response curve. Other researchers have typically framed their aeroelastic uncertainty quantification analysis methods around time-domain aeroelastic solvers, where an indirect measure of aeroelastic stability, such as aeroelastic damping, is the dependent variable that one performs an uncertainty quantification analysis for. Our method allows one to determine directly, uncertainty quantification for an aeroelastic limit cycle oscillation response curve, as well as unstable branches of an aeroelastic limit cycle oscillation response curve. We demonstrate the technique for uncertainty in freestream Mach number and airfoil static unbalance for a two-dimensional model of the NASA Benchmark Models Program B0012 NACA 0012 airfoil section aeroelastic wing configuration.
