Features of panel flutter response to shock boundary layer interactions

The compounding effects of panel flutter and oblique shock impingement are of great concern to the development of light-weight, high-speed vehicles. Shock-induced panel flutter response is investigated at M = 2 and R e = 120 , 000 using the Navier–Stokes equations closely coupled to the von-Kármán equations. A naturally occurring laminar inflow boundary layer and incident oblique shockwave are specified through the boundary conditions. The shockwave impinges at the midpoint of a flexible panel. Several incident shock strengths and non-dimensional dynamic pressures are examined. The resulting fluid–structure interaction is significant and is described in detail. In general, the incident shockwaves lead to higher frequency, higher mode flutter when compared to the configuration without an impinging shockwave or with an impinging shockwave in inviscid flow . Additionally, the presence of a compliant surface is shown to promote turbulent transition downstream of the shock boundary layer interaction.