Development of an unsteady wind tunnel experiment for vortex dominated flow at a Lambda – wing

Abstract

A half wing model, a test rig and new wind tunnel walls were designed to study the vortex development at a lambda wing. It has a sweep angle of 53° and round leading edges. It is designed for pitching oscillations around a mean angle of attack of up to 20°, up to a Mach number of 0.7. Unsteady aerodynamic load data shall be delivered for aeroelastic calculations of Unmanned Combat Aerial Vehicles (UCAV). Due to the highly nonlinear aerodynamic character, the design of the model had to take into account load cases with beginning and fully developed vortices. Furthermore, the different character at subsonic and transonic speeds had to be included. Coupled simulations with a finite element model including the mounting and the connection to the actuation system were performed to assess the dynamic stability. An optimized peniche reduces wing–wall interferences. The test concept and the process of the design will be described.