Computational Aerodynamics: FSI in Plasma Actuated Oscillating Airfoil. Application to macro and micro aerial vehicles

      Аннотация: Today, aviation and aerospace science and industry is proposed as one of the indices of the scientific and technical level of countries, and also plays an important role in the safety of a country. Thus, efforts to promote industrial capabilities in this context is highly recommended by various countries. One of the important things that must be considered in designing aerial structures, in particular the aircraft wings, is interaction between the air and the elastic aircraft wing that is known as the aeroelastic phenomenon. In this book, a numerical study of two dimensional laminar incompressible flow around the oscillating NACA0012 airfoil is proceeded by using OpenFOAM. Oscillatory motion types including pitching, plunging and flapping is considered. Boundary layer control is an useful technique that can improve the aerodynamic performance of the airfoil and it can cause a delay in the stall, for higher angles of attack. Thus, for flow control on airfoil, Dielectric Barrier Discharge plasma actuator as used in two positions on the airfoil and the results obtained from imposing it for each three types of oscillating motion are compared.

Ключевые слова: Fluid-structure interaction, Pitching, plasma, flapping, plunging.