Numerical Simulation on Plasma Circulation Control Airfoil

摘要

A novel plasma circulation control technique is proposed to overcome the disadvantage of conventional jetncirculation control about the requirement for air source.By employing the plasma actuator on the trailing edge of thenairfoil, the plasma-inducedwall jet is tangential to the airfoil surface and served asCoanda blowing jet,whichmakesnthe trailing-edge detachment pointmigrate to the lower surface of the airfoil. In thisway, the circulation and the lift ofnairfoil are directly controlled by the plasma actuator. The effectiveness of plasma circulation control on thenaerodynamic characteristics improvement of NCCR 1510-7067N airfoil is demonstrated by solving the Reynolds-naveraged Navier–Stokes equations. The plasma actuator is modeled with a phenomenological model by adding thenbody force source terms to the governing equations. The results indicate that the efficiency of plasma circulationncontrol for lift augmentation is superior to that of conventional jet circulation controlmethod. The lift augmentationnefficiency after the location optimization reaches u0001CL=Cu0001 u0001 134:86, which is much higher than the maximum liftnaugmentation efficiency 80 for conventional jet circulation control. The optimal location for the plasma actuator innplasma circulation control is downstream of the boundary-layer separation point with proper distance, where thenplasma actuator makes the separated shear layer reattach to the airfoil surface and delays the trailing-edgenstagnation by Coanda effect.