抄録
In this research, a polynomial chaos method is utilized for aerodynamic uncertainty analysis of 2D supersonic biplane airfoil. In this method, all uncertain variables / parameters are replaced with a set of orthogonal polynomials, and then governing equations are expanded for each random mode. Finally, uncertainty analysis can be performed efficiently by solving the expanded governing equations directly. The input uncertainties are given on the freestream Mach number and angle of attack as normal distributions. The stochastic distributions of static pressure of the polynomial chaos method show qualitative agreements with full non-linear Monte-Carlo simulation result. The obtained probability density functions of aerodynamic coefficients also show qualitative agreements with that of Monte-Carlo simulation by increasing the order of polynomial chaos.
