THE STUDY OF FLOW OVER OSCILLATING AIRFOILS AND AIRFOILS WITH TRAILING-EDGE FLAP
振动翼型和襟翼的绕流特性研究

The dynamic precess was numerically simulated on a two dimensional oscillating airfoil or an airfoil with trailing-edge flap in pitch. The Euler and Navier-Stokes equations with Baldwin-Lomax turbulent model were required to solve using the implicit fac-torized finite difference algorithm(LU-AD1 algorithm), which was constructed n a body fitted coordinate system. The study was focused on the unsteady effect of shock wave and control of separation on the lifting surface due to the oscillation. The numerical results have shown that; (1) with the oscillation of the airfoil or trailing-edge flap the shock wave strength and its location are nonlinear response to the morion of lifting surface; (2) the larger the amplitude of oscillation, the more seriously the strength of the shock wave and its location vary; (3) the higher the reduced frequence, the less its influence on variable pressure jump; (4) the characteristics of lift force loop is determined by viscous effect; (5) the oscillating motion can control the separation and augment the lift force.