Nonlinear Reduced-Order Modeling of Limit Cycle Oscillations of Aircraft Wings and Wing/Store

摘要

Significant progress has been made by the ZONA-Duke team in Phase II of our work. A novel and computationally efficient method for calculating transonic limit cycle oscillations (LCO), flutter and other nonlinear aeroelastic phenomena has been developed. To solve the general 3D Euler and Reynolds Averaging Navier-Stokes( Eulen/RANS) equation, a Harmonic Balance(HB) method formulated in the frequency domain in combination with a proper ormogonal decomposition (POD) technique and reduced order modeling (ROM) has been developed and demonstrated on several challenging examples relevant to the Air Force. Various 2D and ID cases for Eulen/RANS have been studied including the conventional NACA 64AlO airfoil, the supercritical NAL73Ol airfoil, the AGARD 445.6 wing and the F-16 wing/store system with the actual structural modes provided by an industry/Air Force team.